Patent Application
20240009806
The present disclosure relates to a thrust reduction system for reducing thrust produced by a blast nozzle during pneumatic blasting.
Any references to methods, apparatus or documents of the prior art are not to be taken as constituting any evidence or admission that they formed, or form, part of the common general knowledge.
It is known to provide a blasting apparatus in which particles of abrasive material entrained in a stream of pressurised gas, most usually air, are expelled from a nozzle in a high velocity jet of the air that is directed onto a surface in order that the particles forcibly impact the surface to clean and/or abrade the surface.
One historically used abrasive material is sand, and when sand is used the blasting process may be referred to as sand blasting. However, other abrasive materials may be used, and garnet is often preferred to silica sand.
The nozzle used as part of the blasting apparatus comprises a body of hardwearing material through which a conduit for the stream of pressurised gas is formed. Commonly, the conduit is shaped so that the nozzles are comprised of a converging inlet portion, which includes an inlet opening for coupling to a source of the pressurised gas such as a blast pot. The inlet portion converges to a throat from which an outlet portion of the conduit extends to a nozzle outlet. The convergence of the inlet portion to the throat raises the velocity of the pressurised gas to approximately sonic speeds. The outlet portion may be formed to diverge from the throat to the nozzle outlet in order to further increase the velocity of the air so that the jet that is emitted from the nozzle outlet is at a high velocity.
The high pressure and air flows used in abrasive blasting produce thrust, indicated by arrows 4 in the opposite direction to the flow of the blast stream, being the jet 13. The force of this blast nozzle thrust 4, sometimes referred to as nozzle kick back, varies depending on nozzle size, such as nozzle 1, and inlet pressure and can range from around 6 kg for a No. 6 nozzle to more than 17 kg for a No. 10 nozzle when operated at an inlet pressure of 100 psi. Operators, i.e. the worker who holds the nozzle 1, are required to resist the blast nozzle thrust 4 during blasting processes, which can lead to operator fatigue, reduced productivity and stress related injuries due to extended use.
Blast nozzle thrust is inherent with the operation of all blast nozzles. The reduction of blast nozzle thrust has not been adequately addressed and remains problematic for blasting operators and the industry more broadly.
It is an object of the present disclosure to provide method and apparatus for reducing blast nozzle thrust.
In one aspect there is provided a blast nozzle blast thrust reduction apparatus for connection to a blast nozzle, including a body defining a conduit extending from an inlet of the thrust reduction apparatus to an outlet of the thrust reduction apparatus, the body being of a diameter and length for the conduit to extend a distance from an outlet of the blast nozzle sufficient to reduce the nozzle thrust produced by the jet emitted from the blast nozzle outlet in use.
In an aspect there is provided a blast nozzle thrust reduction blasting system comprising:
In an embodiment the thrust reducer body includes a coupling portion arranged to connect to a portion of the nozzle adjacent the nozzle outlet and a thrust reduction portion defining the thrust reducer conduit, wherein the thrust reduction portion extends from the coupling portion to a thrust reducer outlet of the thrust reducer.
In an embodiment the predetermined pressure range is 80 psi or greater.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of 1.63±5%.
In an embodiment the nozzle comprises a #3 nozzle and the thrust reducer has a thrust reducer outlet diameter of 11.75±2.5% mm and a thrust reduction portion length of 37.50±5% mm.
In an embodiment the nozzle comprises a #4 nozzle and the thrust reducer has a thrust reducer outlet diameter of 15.67±2.5% mm and a thrust reduction portion length of 50.00±5% mm.
In an embodiment the nozzle comprises a #5 nozzle and the thrust reducer has a thrust reducer outlet diameter of 19.58±2.5% mm and a thrust reduction portion length of 62.50±5% mm.
In an embodiment the nozzle comprises a #6 nozzle and the thrust reducer has a thrust reducer outlet diameter of 23.50±2.5% mm and a thrust reduction portion length of 75.00±5% mm.
In an embodiment the nozzle comprises a #7 nozzle and the thrust reducer has a thrust reducer outlet diameter of 27.1±2.5% mm and a thrust reduction portion length of 87.50±5% mm.
In an embodiment the nozzle comprises a #8 and the thrust reducer has a thrust reducer outlet diameter of 31.33±2.5% mm and a thrust reduction portion length of 100±5% mm.
In an embodiment the nozzle comprises a #10 nozzle and the thrust reducer has a thrust reducer outlet diameter of 39.16±2.5% mm and a thrust reduction portion length of 125±5% mm.
In an embodiment the nozzle comprises a nozzle with nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
In an embodiment the nozzle comprises a nozzle with nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of 1.42±5%
In an embodiment the nozzle comprises a nozzle with a nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of 2.1±5%.
In an embodiment the nozzle comprises a nozzle with a nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
In an embodiment the predetermined pressure range is 80 psi or greater and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a nozzle with a nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length ranging between the preferred length and the minimum length for effective thrust reduction as set out in the following table for the nozzle size:
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #3 nozzle and wherein the length of the thrust reducer is between 7.5 mm and 67.5 mm and the diameter of the thrust reducer is between 10.00 mm and 13.5 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #4 nozzle and wherein the length of the thrust reducer is between 10.0 mm and 90 mm and the diameter of the thrust reducer is between 13 mm and 18 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #5 nozzle and wherein the length of the thrust reducer is between 12.5 mm and 112.5 mm and the diameter of the thrust reducer is between 12.5 mm and 22.5 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #6 nozzle and wherein the length of the thrust reducer is between 15 mm and 135.0 mm and the diameter of the thrust reducer is between 20 mm and 27.1 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #7 nozzle and wherein the length of the thrust reducer is between 17.5 mm and 157.5 mm and the diameter of the thrust reducer is between 23 mm and 31.5 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #8 nozzle and wherein the length of the thrust reducer is between 20.0 mm and 179.5 mm and the diameter of the thrust reducer is between 26.5 mm and 36.0 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #10 nozzle and wherein the length of the thrust reducer is between 25 mm and 224.5 mm and the diameter of the thrust reducer is between 33.0 mm and 45.0 mm.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of between 1.42 and 2.1 and wherein the nozzle comprises a #3 nozzle and the silencer has a silencer outlet diameter of between 10 mm and 13.6 mm and a minimum sound suppression portion length of between 7.5 mm and 78.5 mm.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of between 1.42 and 2.1 and wherein the nozzle comprises a #4 nozzle and the silencer has a silencer outlet diameter of between 12.4 mm and 18.1 mm and a minimum sound suppression portion length of between 10 mm and 104 mm.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of between 1.42 and 2.1 and wherein the nozzle comprises a #5 nozzle and the silencer has a silencer outlet diameter of between 15.5 mm and 22.6 mm and a minimum sound suppression portion length of between 12.5 mm and 130.5 mm.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of between 1.42 and 2.1 and wherein the nozzle comprises a #6 nozzle and the silencer has a silencer outlet diameter of between 18.5 mm and 27.1 mm and a minimum sound suppression portion length of between 15 mm and 157 mm.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of between 1.42 and 2.1 and wherein the nozzle comprises a #7 nozzle and the silencer has a silencer outlet diameter of between 21.7 mm and 31.6 mm and a minimum sound suppression portion length of between 17.5 mm and 183 mm.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of between 1.42 and 2.1 and wherein the nozzle comprises a #8 nozzle and the silencer has a silencer outlet diameter of between 24.8 mm and 36.1 mm and a minimum sound suppression portion length of between 20 mm and 209 mm.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of between 1.42 and 2.1 and wherein the nozzle comprises a #10 nozzle and the silencer has a silencer outlet diameter of between 31.0 mm and 45.2 mm and a minimum sound suppression portion length of between 25 mm and 261 mm.
In an embodiment the coupling portion comprises a female thread.
In an embodiment the thrust reducer body includes an inlet body portion that is removably received within the thrust reducer conduit of the thrust reducer body.
In an embodiment the inlet body portion comprises a removable sleeve that is removably received within the body.
In another aspect there is provided a method for reducing blast nozzle thrust of a blast nozzle, the method comprising:
In an embodiment the thrust reducer body includes a coupling portion arranged to connect to a portion of the nozzle adjacent the nozzle outlet and a thrust reduction portion defining the thrust reducer conduit, wherein the thrust reduction portion extends from the coupling portion to a thrust reducer outlet of the thrust reducer.
In an embodiment the predetermined pressure range is 80 psi or greater.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of 1.63±5%.
In an embodiment the nozzle comprises a #3 nozzle and the thrust reducer has a thrust reducer outlet diameter of 11.75±2.5% mm and a thrust reduction portion length of 37.50±5% mm.
In an embodiment the nozzle comprises a #4 nozzle and the thrust reducer has a thrust reducer outlet diameter of 15.67±2.5% mm and a thrust reduction portion length of 50.00±5% mm.
In an embodiment the nozzle comprises a #5 nozzle and the thrust reducer has a thrust reducer outlet diameter of 19.58±2.5% mm and a thrust reduction portion length of 62.50±5% mm.
In an embodiment the nozzle comprises a #6 nozzle and the thrust reducer has a thrust reducer outlet diameter of 23.50±2.5% mm and a thrust reduction portion length of 75.00±5% mm.
In an embodiment the nozzle comprises a #7 nozzle and the thrust reducer has a thrust reducer outlet diameter of 27.1±2.5% mm and a thrust reduction portion length of 87.50±5% mm.
In an embodiment the nozzle comprises a #8 and the thrust reducer has a thrust reducer outlet diameter of 31.33±2.5% mm and a thrust reduction portion length of 100±5% mm.
In an embodiment the nozzle comprises a #10 nozzle and the thrust reducer has a thrust reducer outlet diameter of 39.16±2.5% mm and a thrust reduction portion length of 125±5% mm.
In an embodiment the nozzle comprises a nozzle with nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
In an embodiment the nozzle comprises a nozzle with nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of 1.42±5%
In an embodiment the nozzle comprises a nozzle with a nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of 2.1±5%.
In an embodiment the nozzle comprises a nozzle with a nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
In an embodiment the predetermined pressure range is 80 psi or greater and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a nozzle with a nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length ranging between the preferred length and the minimum length for effective thrust reduction as set out in the following table for the nozzle size:
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #3 nozzle and wherein the length of the thrust reducer is between 7.5 mm and 67.5 mm and the diameter of the thrust reducer is between 10.00 mm and 13.5 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #4 nozzle and wherein the length of the thrust reducer is between 10.0 mm and 90 mm and the diameter of the thrust reducer is between 13 mm and 18 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #5 nozzle and wherein the length of the thrust reducer is between 12.5 mm and 112.5 mm and the diameter of the thrust reducer is between 12.5 mm and 22.5 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #6 nozzle and wherein the length of the thrust reducer is between 15 mm and 135.0 mm and the diameter of the thrust reducer is between and 27.1 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #7 nozzle and wherein the length of the thrust reducer is between 17.5 mm and 157.5 mm and the diameter of the thrust reducer is between 23 mm and 31.5 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #8 nozzle and wherein the length of the thrust reducer is between 20.0 mm and 179.5 mm and the diameter of the thrust reducer is between 26.5 mm and 36.0 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #10 nozzle and wherein the length of the thrust reducer is between 25 mm and 224.5 mm and the diameter of the thrust reducer is between 33.0 mm and 45.0 mm.
In an embodiment the coupling portion comprises a female thread.
In an embodiment the thrust reducer body includes an inlet body portion that is removably received within the thrust reducer conduit of the thrust reducer body.
In an embodiment the inlet body portion comprises a removable sleeve that is removably received within the body.
In another aspect there is provided a thrust reducer arranged to connect to and reduce s operational thrust of a blast nozzle, the blast nozzle comprising a body with a conduit therethrough extending from a nozzle inlet for connection to a source of blasting gas and a nozzle outlet for emitting a jet, the nozzle conduit including a throat between the nozzle inlet and the nozzle outlet, the nozzle outlet having a nozzle outlet area and the throat having a throat area, a ratio of the nozzle outlet area to the throat area constraining the nozzle to produce a supersonic jet,
In an embodiment the thrust reducer body includes a coupling portion arranged to connect to a portion of the nozzle adjacent the nozzle outlet and a thrust reduction portion defining the thrust reducer conduit, wherein the thrust reduction portion extends from the coupling portion to a thrust reducer outlet of the thrust reducer.
In an embodiment the predetermined pressure range is 80 psi or greater.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of 1.63±5%.
In an embodiment the nozzle comprises a #3 nozzle and the thrust reducer has a thrust reducer outlet diameter of 11.75±2.5% mm and a thrust reduction portion length of 37.50±5% mm.
In an embodiment the nozzle comprises a #4 nozzle and the thrust reducer has a thrust reducer outlet diameter of 15.67±2.5% mm and a thrust reduction portion length of 50.00±5% mm.
In an embodiment the nozzle comprises a #5 nozzle and the thrust reducer has a thrust reducer outlet diameter of 19.58±2.5% mm and a thrust reduction portion length of 62.50±5% mm.
In an embodiment the nozzle comprises a #6 nozzle and the thrust reducer has a thrust reducer outlet diameter of 23.50±2.5% mm and a thrust reduction portion length of 75.00±5% mm.
In an embodiment the nozzle comprises a #7 nozzle and the thrust reducer has a thrust reducer outlet diameter of 27.1±2.5% mm and a thrust reduction portion length of 87.50±5% mm.
In an embodiment the nozzle comprises a #8 and the thrust reducer has a thrust reducer outlet diameter of 31.33±2.5% mm and a thrust reduction portion length of 100±5% mm.
In an embodiment the nozzle comprises a #10 nozzle and the thrust reducer has a thrust reducer outlet diameter of 39.16±2.5% mm and a thrust reduction portion length of 125±5% mm.
In an embodiment the nozzle comprises a nozzle with nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
In an embodiment the nozzle comprises a nozzle with nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of 1.42±5%.
In an embodiment the nozzle comprises a nozzle with a nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of 2.1±5%.
In an embodiment the nozzle comprises a nozzle with a nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter as set out in the following table for the nozzle size and thrust reduction portion length at least as long as set out in the following table for the nozzle size:
In an embodiment the predetermined pressure range is 80 psi or greater and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a nozzle with a nozzle size as set out in the leftmost column of the following table and the thrust reducer has a thrust reducer outlet diameter 10 as set out in the following table for the nozzle size and thrust reduction portion length ranging between the preferred length and the minimum length for effective thrust reduction as set out in the following table for the nozzle size:
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #3 nozzle and wherein the length of the thrust reducer is between 7.5 mm and 67.5 mm and the diameter of the thrust reducer is between 10.00 mm and 13.5 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #4 nozzle and wherein the length of the thrust reducer is between 10.0 mm and 90 mm and the diameter of the thrust reducer is between 13 mm and 18 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #5 nozzle and wherein the length of the thrust reducer is between 12.5 mm and 112.5 mm and the diameter of the thrust reducer is between 12.5 mm and 22.5 mm.
In an embodiment wherein the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #6 nozzle and wherein the length of the thrust reducer is between 15 mm and 135.0 mm and the diameter of the thrust reducer is between 20 mm and 27.1 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #7 nozzle and wherein the length of the thrust reducer is between 17.5 mm and 157.5 mm and the diameter of the thrust reducer is between 23 mm and 31.5 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #8 nozzle and wherein the length of the thrust reducer is between 20.0 mm and 179.5 mm and the diameter of the thrust reducer is between 26.5 mm and 36.0 mm.
In an embodiment the predetermined pressure range is 80 psi to 120 psi and the nozzle has an A/A* area ratio of 1.63±5% wherein the nozzle comprises a #10 nozzle and wherein the length of the thrust reducer is between 25 mm and 224.5 mm and the diameter of the thrust reducer is between 33.0 mm and 45.0 mm.
In an embodiment the coupling portion comprises a female thread.
In an embodiment the thrust reducer body includes an inlet body portion that is removably received within the thrust reducer conduit of the thrust reducer body.
In an embodiment the inlet body portion comprises a removable sleeve that is removably received within the body.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of between 1.42 and 2.1 and wherein the nozzle comprises a #3 nozzle and the silencer has a silencer outlet diameter of between 10 mm and 13.6 mm and a minimum sound suppression portion length of between 7.5 mm and 78.5 mm.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of between 1.42 and 2.1 and wherein the nozzle comprises a #4 nozzle and the silencer has a silencer outlet diameter of between 12.4 mm and 18.1 mm and a minimum sound suppression portion length of between 10 mm and 104 mm.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of between 1.42 and 2.1 and wherein the nozzle comprises a #5 nozzle and the silencer has a silencer outlet diameter of between 15.5 mm and 22.6 mm and a minimum sound suppression portion length of between 12.5 mm and 130.5 mm.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of between 1.42 and 2.1 and wherein the nozzle comprises a #6 nozzle and the silencer has a silencer outlet diameter of between 18.5 mm and 27.1 mm and a minimum sound suppression portion length of between 15 mm and 157 mm.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of between 1.42 and 2.1 and wherein the nozzle comprises a #7 nozzle and the silencer has a silencer outlet diameter of between 21.7 mm and 31.6 mm and a minimum sound suppression portion length of between 17.5 mm and 183 mm.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of between 1.42 and 2.1 and wherein the nozzle comprises a #8 nozzle and the silencer has a silencer outlet diameter of between 24.8 mm and 36.1 mm and a minimum sound suppression portion length of between 20 mm and 209 mm.
In an embodiment the nozzle has a nozzle exit area to nozzle throat area ratio (A/A*) of between 1.42 and 2.1 and wherein the nozzle comprises a #10 nozzle and the silencer has a silencer outlet diameter of between 31.0 mm and 45.2 mm and a minimum sound suppression portion length of between 25 mm and 261 mm.
Further features and embodiments will be described in the detailed description that follows. For example, thrust reduction apparatus according to the various dimensions and to suit the various nozzle sizes that will be described comprise embodiments of aspects of the present disclosure.
Embodiments in accordance with the present disclosure will be described, by way of example, in the following Detailed Description of Embodiments which provides sufficient information for those skilled in the art to perform the subject matter that is disclosed herein. The Detailed Description of Embodiments is not to be regarded as limiting the scope of the preceding Summary section in any way. The Detailed Description will make reference to the accompanying drawings, by way of example, in which:
The dimensions in the Figures are in mm and are exemplary only and non-limiting.
Whilst the following discussion pertains to jets composed of gas, the inventors have observed nozzle flows for both gas only (for example, air), and particle laden flows (air containing abrasive particles) and noted similar flow structures with the aid of high speed optical imaging.
The described effects have been experimentally measured for gas only and particle laden flows.
Blast nozzles such as the blast nozzle of
Blast nozzles are generally very noisy during operation, and it is known to provide silencers for blast nozzles, such as the nozzle 1 of
A new and surprising feature of the silencers produced during this process became apparent as the prototype silencers were tested. Operators reported a significant reduction in blast nozzle thrust when testing the nozzle with the silencer connected compared to when testing the nozzle without the silencer. Whilst not in the original scope of the silencer development project, it became clear that the unexpected benefits associated with the observed reduction in blast nozzle thrust were significant.
Blast nozzles are typically sized by their throat diameter in fractions of an inch, e.g. a #6 blast nozzle has a throat diameter of 6/16″ whereas a #3 blast nozzle has a throat diameter of 3/16″.
The blast nozzle 100 is formed with a conduit 102 therethough for accelerating air with abrasive particles at a predetermined pressure. In the present case nozzle 100 is designed for an inlet air pressure of 80 to greater than 120 psi and nominally 100 psi to discharge to sea level ambient atmospheric pressure at 27 degrees C. The pressurised air contains abrasive particles such as #80 Garnet to abrade a workpiece. The conduit 102 includes an inlet portion 104 that converges from an inlet opening 106, for receiving the compressed air, to a throat 116 for accelerating the air to a sonic speed. The inlet portion 104 may generally follow a concave-convex curve, as illustrated, with an initial concave portion 110 that proceeds through an inflection point 112 to a convex portion 114. The convex portion 114 ends in a throat 116, of zero axial length along the conduit, from which an outlet portion 118 extends. The outlet portion 118 diverges from the throat 116 to a nozzle outlet 120, of diameter Do, for accelerating the air from the throat 116 to a super-sonic speed. It should be realised that while it is preferable to make use of an inlet portion shaped with a concave-convex curve it is not essential to do so and blast nozzles with other shaped inlets, for example frusto-conical inlets are also workable.
It is known that an ideally expanded supersonic jet can be produced by a converging/ expanding blast nozzle when operated at the design inlet pressure for the specific nozzle exit to nozzle throat area ratio (A/A*) such as the nozzle discussed in the international patent application No. PCT/AU2021/050827. Other blast nozzle geometries will produce an ideally expanded jet when operated at the ideal supply pressure for the particular nozzle exit to nozzle throat area ratio A/A*. Table 2 lists the exit Mach number, ideal pressure ratio and ideal supply pressure (P design) pressure for a range of nozzle A/A* ratios. The ideal supply pressure is the pressure at which a nozzle with a A/A* area ratio creates an ideally expanded jet.
It is also known that nozzles as described, when operated at the ideal supply pressure,
It is also known that when nozzle inlet pressure increases above the ideal supply pressure for the a given nozzle A/A* ratio, the supersonic jet that is produced will progressively become more underexpanded and when the nozzle inlet pressure decreases below the ideal supply pressure for the a given nozzle A/A* ratio, the supersonic jet that is produced will progressively become more overexpanded. Overexpanded and underexpanded supersonic jets are more turbulent than ideally expanded jets and the jet structure breaks down at a shorter distance after the nozzle exit compared to an ideally expanded jet.
A ratio of the area A of the nozzle outlet 120 to area A* of the throat 116 a (A/A*) is selected for expansion of the air through the nozzle 100 so it is neither under-expanded nor overexpanded as it exits the outlet 120 but rather is “ideally” expanded. The area ratio is about 1.63 for compressed air applied in the range of 80 psi to 120 psi above ambient pressure and optimally 100 psi. Accordingly, the pressurised air exits the nozzle outlet 120 in a jet at ambient pressure. The jet imparts drag on the abrasive particles between the nozzle outlet and the workpiece. Consequently, the energy of the particles is increased over the standoff distance between the nozzle outlet 120 and the surface of the workpiece. The standoff distance is typically around 350 mm to 600 mm from the nozzle outlet to the workpiece in use. Consequently, nozzles according to embodiments herein are more effectively able to clean/abrade the surface of the workpiece than a nozzle designed to work in an overexpanded or underexpanded mode.
The dimensions for a #6 blast nozzle as illustrated are set out in the third rows of the tables of
In determining the optimal nozzle length, it was found that for a #6 nozzle 220 mm was the best length from testing with #60/30 garnet (0.3 mm particle size, 4100 1 g/m3 density). The optimal length for a #6 nozzle may be longer in other embodiments such as 300 mm. There may be other considerations, such as access and ergonomics, which limit the utility of a longer nozzle. In general, longer nozzles are better suited to larger, heavier abrasive blends, whilst shorter nozzles are better suited for lighter and smaller blends. A preferred range on the diverging section length L for embodiments of the nozzle is 70-300 mm.
It is known that a blast nozzle thrust force in the opposite direction to the flow of a jet, identified by arrows 4 in
The Inventors hypothesised that if the jet exiting the blast nozzle could be modified in such a way to produce an anti-thrust force in in the direction to the flow of the jet, in opposition to the primary force generated by the flow of the jet, reduced nozzle thrust would be generated during the blasting process and then reduced effort would need to be applied by the operator to resist this force.
As will be discussed, the Inventors found that useful nozzle thrust reduction continues to occur for nozzles that are operated at above or below the nozzle design pressure (P_design) i.e., overexpanded or underexpanded jets produced by a nozzle without the thrust reduction device, but the effectiveness of the thrust reduction will be reduced as operation pressure reduces. The limiting minimum pressure for reliable thrust reduction to occur for a nozzle with an area ratio A/A* of 1.42 is 50 psi±5%, with an A/A* of 1.63 is 65 psi±5% and with an A/A* of 2.1 is 100 psi±5%. As inlet pressure increases and the jet becomes more underexpanded, effective thrust reduction continues to occur up to the practical limitation for typical blasting systems—currently 150 psi.
As previously alluded to, the Inventors have discovered that blast nozzle thrust can be reduced. A parameter that has been found to be essential for creating the zone of low sub-atmospheric pressure is the formation of the first half shock diamond that reflects inside the thrust reducer that is created in the modified jet that enters the thrust reducer.
The Inventors have previously found that nozzle silencing occurs when a silencer of sufficient length and diameter to cause the flow condition of the jet received from the exit of the blast nozzle to be modified such that 1 ½ shock cells are created in the jet inside the silencer, no shock cells are created in the jet outside the silencer, and the jet exits the silencer with an established turbulent shear layer, and the jet entrains an annular jet that sits around the outside of the core jet, to thereby enclose and suppress an acoustic emission region of the jet, which is the area from which “screech” and broadband tones are generated.
As will be discussed, the Inventors have found that an apparatus may be provided which provides some thrust reduction alone or an apparatus may be provided which provides both some thrust reduction and some noise suppression characteristics. Both versions are useful.
Accordingly, as illustrated in
The pressure differential 218 creates a force 220 in the opposite direction to the blast nozzle thrust 224. The force 220 in the opposite direction to the blast nozzle thrust 224 is due to the pressure differential 218. Namely, the pressure of the external atmosphere 226, which is greater than the pressure in the zone of sub-atmospheric pressure, applied to external surfaces of the nozzle, thrust 10 reducer and hose, urges the face 214 of the nozzle 100 toward the zone of sub-atmospheric pressure 212 thereby resulting in an anti-thrust force 220, which acts in opposite direction to the thrust force 214 thereby resulting in a reduced net thrust being applied to an operator of the nozzle.
As the jet 200 exits the nozzle 205 the combined effects of jet expansion, entrainment (driven by momentum exchange) and balance of momentum reduce pressure in the zone of sub-atmospheric pressure 212. This combination of effects is enhanced by the expansion and an oblique shock interaction in region 213, which assists in preventing back-flow and separates the low-pressure region 212 from the outlet (far right hand side in
Pressure equalisation between the zone of sub-atmospheric pressure 212 and atmosphere 226 is prevented when the conduit diameter and length (or shape of the conduit more generally) are such that the jet 200 and internal wall of the conduit 228 interact in such a way as to effectively close the pathway for pressure to equalise to atmosphere. As a secondary effect this may cause a flow recirculation in the zone of sub-atmospheric pressure 212 and is bounded by the face 214 of the exit end of the nozzle 214, the internal wall 228 of the conduit 210 and the boundary of the supersonic jet 200 from the nozzle exit 216 to region 213, where it interacts with the internal wall of the conduit 228. The ability for pressure in the zone of sub-atmospheric pressure 212 to equalise to atmosphere 226 is reduced as the interaction of the jet and the conduit wall increases. Pressure equalisation is prevented when the interaction of the jet 200 and the conduit wall 228 becomes strong enough, e.g. at region 213, to close or “seal off” a pathway for air to enter the zone of sub-atmospheric pressure from outside the conduit. When this occurs flow recirculation in the zone of sub-atmospheric pressure can begin to occur.
As the ability for pressure equalisation reduces, pressure differential increases. The maximum pressure differential occurs when the air pathway is “sealed” and flow recirculation occurs. Sub-atmospheric pressure is maintained in the zone of sub-atmospheric pressure 212 during blasting, creating a pressure differential 218 to atmosphere acting on the area of the face 214 of the exit end 10 of the nozzle exposed to the zone of sub-atmospheric pressure and producing a constant force 220 acting in the opposite direction to the blast nozzle thrust 224.
It should be noted that if the geometry of the thrust reduction device is such that the diameter is too large or the length is too short—not in accordance with the design disclosed, or the operating pressure is too low, this will result in the interaction of the expansion and the oblique shock of the jet 200 with the internal wall of the conduit 228 to weaken, and entrainment along the conduit wall from the conduit outlet will begin to occur. Pressure in the zone of sub-atmospheric pressure 212 remains sub-atmospheric and will increase as entrainment increases. The resultant pressure differential in the zone of sub-atmospheric pressure 212 reduces along with the force acting in the opposite direction to the blast nozzle thrust 220. Blast Nozzle thrust reduction force (indicated by arrow 220 in
Referring now to
With reference to
The magnitude of the thrust reduction force 220 is dependent on operating inlet pressure, nozzle exit diameter, surface area of the face of the nozzle exit exposed to the zone of sub-atmospheric pressure, geometry of the area of the conduit immediately connected to the exit of the nozzle and can be approximated using the following formula:
Thrust reduction force=(P_atmospheric−P_end)*(Area_conduit_internal−Area_nozzle_exit internal) where P_end is the pressure measured on the face of the nozzle exit, i.e. the pressure in the zone of sub-atmospheric pressure 212. It should be noted that the face of the nozzle exit 214 need not be perpendicular to the longitudinal axis of the conduit of the thrust reducer in order for the sub-atmospheric zone 212 to arise. The face of the corner of the nozzle exit 214 needs to be sufficiently sharp at this location so that an expansion fan forms and creates a sub-atmospheric pressure zone adjacent to the face of the nozzle exit when operated with the thrust reduction device fitted. This sub- atmospheric pressure zone is required for the first expansion wave to form enabling the development of the desired flow pattern described above. This will be achieved by a “rectangular/radial” face. However, the same will also be true for a backwards sloped face and some forward sloping faces. The thrust reduction effect effect will stop once the face becomes so far forward sloping that the thrust reduction device simply becomes an extension of the nozzle, that is a continuation of the expanding section. In this case the expansion will continue, or the flow will separate without the formation of a discrete low-pressure region. Having a near rectangular face is likely to be favourable for thrust reduction when operated at pressures greater than P*, as it makes establishment of the sub atmospheric pressure zone favourable and it is easy to manufacture.
Approximated thrust reduction force 220 for standard size nozzles when Pend takes an exemplary pressure of 10 kPa (absolute), as observed in simulations is shown below. Note, 10 kPa (absolute) is an exemplary value only to illustrate the thrust reduction potential. Reduction in thrust force based on P_end=10 kPa (absolute) for different nozzle sizes are set out in the table in
It follows that thrust reduction is also increased as the surface area exposed to P_end is increased (i.e. Area_conduit_internal−Area_nozzle_exit_internal)—as shown in the table of
Results of field experiments are consistent with the above hypothesis. The table of
Through simulation and experiment the Inventors have established that the mechanism for thrust reduction changes as the nozzle length reduces and/or conduit inner diameter increases.
Simulations have shown that this takes place at an internal diameter of 23.5 mm and a length of 40 mm for number 6 nozzles operating at inlet pressure of 80 psi, and experiments have shown this to occur at a length of 35 mm for operation at inlet pressure of 100 psi. After this point density and pressure of air in the zone of sub-atmospheric pressure still reduces however the boundary of the jet no longer fully expands to strongly interact with the internal wall of the conduit (see FIG. 24). However, a reduction in thrust (e.g., 5% for the exemplary data shown in the table) still exists. As a result, pressure in the zone of sub-atmospheric pressure is reduced, but not to the extent as when flow recirculation occurs.
Furthermore, as the jet exiting the nozzle expands to interact with the thrust reduction device wall, other flow features that result in nozzle silencing occur, namely 1 ½ shock cells are created in the jet inside the thrust reduction device, no shock cells are created in the jet outside the thrust reduction device and the jet exits the thrust reduction device with an established turbulent shear layer, and the jet entrains an annular jet that sits around the outside of the core jet, and this is desirable for reducing noise.
To maximise performance (maximum thrust reduction and cleaning rate) at different operating pressures it is necessary to adjust the dimensions of the thrust reduction device. That is, while a thrust reduction device designed for 100 psi (nominal design point) will still provide thrust reduction at 80 psi, to achieve maximum performance the thrust reduction device dimensions should be adjusted (shorter and smaller diameter).
Thrust reduction device geometries for effective thrust reduction are set out in Table 3 to Table 11 for a nozzle with an area ratio of 1.63±5%. The tables show examples of preferred thrust reduction device lengths and diameters, diameters and minimum lengths for effective thrust reduction for a range of pressures at which thrust reduction becomes effective (P*).
Effective Thrust reduction continues to occur at lengths longer than the minimum effective length. The length of the Thrust reduction device above this minimum length is constrained by the practical constraints for the blasting application.
The following table—Table 12 describes the preferred Thrust reduction device geometry, meaning it gives robust performance and considers other factors relevant to blasting along with effective thrust reduction. The following two examples in the table correspond to relevant geometries that provide effective thrust reduction when operated at 100 psi (P_Design inlet pressure). This provides coverage of relevant geometries that would be effective and that could be considered useful in a blasting application when operated at the 100 psi nozzle inlet pressure. This provides a lower and upper bound to the Thrust reduction device geometries that could be considered effective when blasting using a nozzle with an area ratio A/A* of 1.63±5%.
It is known that abrasive blasting nozzles can have a range of area ratios A/A* other than 1.63 and can be operated at various inlet pressures. The following tables contain dimensions for effective Thrust reduction devices for nozzles with two different area ratios A/A* operated at at range of inlet pressures including 80 psi, 100 psi, 120 psi and 130 psi.
Thrust reduction device geometries for effective thrust reduction are set out in Table 13 to Table 17 for a nozzle with an area ratio of 1.42±5%.
Thrust reduction device geometries for effective thrust reduction are set out in Table 18 to Table 22 for a nozzle with an area ratio of 2.1±5%.
The inventors have tested the effectiveness of thrust reduction devices when operated at inlet pressures other than the ideal supply pressure for the nozzle exit to throat ratio (A/A*) of 1.63 and have found Thrust reduction devices with dimensions as set out in Tables 3 to 12 to be effective when operated at the inlet pressures shown.
Additionally, the inventors have tested thrust reduction device designs for use with nozzle area ratios (A/A*) other than 1.63, including 1.42 and 2.1 and have confirmed thrust reduction device geometries as set out in Tables 13 to 22 to be effective when operated at the inlet pressures shown.
It should be noted that stated thrust reduction device dimensions for operation at standard atmospheric conditions at sea level. Allowance should be made to accommodate differences in atmospheric pressure, temperature and humidity expected during operation.
Effective thrust reduction continues to occur at lengths above the minimum effective length. The length of the thrust reduction device above this minimum length is constrained by the practical constraints for the blasting application.
The Inventors have found a thrust reducer having a body of sufficient length to extend a distance of at least one shock diamond (expansion wave inside the thrust reduction device) from the outlet of the blast nozzle in use produces the thrust reduction effect. By making the body longer, so that it encapsulates at least the first three shock diamonds of a substantially ideally expanded jet from a nozzle without a thrust reduction device fitted, the Inventors have also found that the operational noise, particularly “screech” of the blast jet is substantially reduced so that in that case the thrust reduction apparatus operates both to reduce thrust and also as a silencer.
Additionally, through experiment the inventors have shown that a thrust reduction device with an internal ramp as shown in
In compliance with the statute, the subject matter disclosed herein has been described in language more or less specific to structural or methodical features. The term “comprises” and its variations, such as “comprising” and “comprised of” is used throughout in an inclusive sense and not to the exclusion of any additional features. It is to be understood that the disclosure is not limited to specific features shown or described since the means herein described comprises preferred forms of putting the disclosed subject matter into effect.
| Number | Date | Country | Kind |
|---|---|---|---|
| 2020904468 | Dec 2020 | AU | national |
| 2021902119 | Jul 2021 | AU | national |
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/AU2021/051438 | 12/2/2021 | WO |
| Number | Date | Country | |
|---|---|---|---|
| 63220153 | Jul 2021 | US | |
| 63120418 | Dec 2020 | US |
