The invention relates in general to turbine wheels in gas turbines, and it relates more particularly to axially retaining blades carried by the wheels. The field of application of the invention is in particular that of industrial gas turbines or gas turbine aeroengines.
In a turbine wheel, the blades are mounted at the periphery of a disk, each blade having an airfoil with a foot that is secured to an attachment member that is engaged axially in a housing or slot that opens into the periphery of the disk and that extends between two opposite faces of the disk.
Axial retention devices for blades are necessary to prevent any axial movement due to vibration or to thermal effects and in spite of the pressure that is generated by centrifugal force between the contacting surface portions of the blade attachment members and the housings in the disk.
Known axial retention devices make use of plates carried by the rotor and pressing against upstream (front) and downstream (rear) side faces of the blade attachment members. It is also known from documents WO 99/50534 and WO 99/30008 to use a single plate that presses against the attachment members of the blades on the upstream side, and, on the downstream side, to use a continuous circumferential abutment formed on the disk and pressing against portions in relief formed under the platforms of the blades at the downstream side. In order to reduce overall size, the length of the attachment members (in the axial direction) could be made shorter than that of the housings, with the downstream face of the attachment members being set back from the downstream face of the disk. However the trailing edge of the airfoil of the blade would then be cantilevered-out relative to the attachment member, which member would then be subjected to bending stresses that might weaken it.
An object of the invention is to provide a turbine wheel provided with a system for axially retaining blades that presents minimum overall size without giving rise to excessive loading on the attachment members of the blades.
This object is achieved by a turbine wheel comprising:
in which turbine wheel, the housings for the attachment members of the blades extend axially over the entire distance between the opposite side faces of the disks, and at the second side of the disk, the blades are retained axially by the portions in relief formed under the platforms of the blades pressing axially against portions in relief formed on the teeth of the disk, the axial pressure being set back relative to the side faces of the attachment members situated on the second side of the disk, and the side faces of the attachment members of the blades and of the disk at the periphery thereof are situated substantially in a same plane.
Thus, advantageously, axial overall size is minimized and the trailing edge at the base of each airfoil need not be significantly cantilevered-out relative to the attachment member of the airfoil.
Preferably, axial pressure between a blade and a corresponding tooth of the disk is applied substantially level with the suction side face of the airfoil, and under the foot of the airfoil.
Preferably, the retaining plate exerts axial pressure on the side faces of the teeth of the disk or of the attachment members of the blades. The retaining plate advantageously presents a radial dimension that is limited so as to press solely against the bottom portions of the teeth of the disk or of the attachment members of the blades.
Axial pressure may advantageously be provided and maintained between the blades and the rotor without encroaching on the radial clearance between the rotor and an adjacent stator.
Advantageously, the retaining plate presents extra thickness at its periphery forming a cantilevered-out mass. During rotation, it is thus possible to avoid the plate opening and giving rise to a loss of pressure from the plate.
The retaining plate may press against the side faces of the teeth of the disk or of the attachment members of the blades with prestress.
The retaining plate may be mounted on the rotor, while being held axially by means of a retaining split ring.
Advantageously, at least one opening forming an inspection window is formed in the rotor to enable the positioning of the retaining split ring to be inspected visually.
The invention also provides a turbomachine including a turbine wheel according to the invention.
The invention can be better understood on reading the following description made with reference to the accompanying drawings, in which:
Each of the blades 20 (see also
Each blade 20 has its foot secured to a platform 24 that carries an attachment member (or tang) 26 serving to connect the blade to the disk 12. In the example shown, the attachment member has a fir-tree shaped profile. The platforms 24 of the blades define the passage 30 on the internal side.
The attachment members 26 are engaged axially in housings (or slots) 14 of complementary shape that are distributed around and open to the periphery of the disk 10. The housings 14 extend axially over the entire distance between the upstream (or front) side face 12a and the downstream (or rear) side face 12b of the disk, and they are separated from one another by teeth 16 of the disk. The terms “upstream” and “downstream” are used herein relative to the flow direction of the gas stream through the turbine.
Downstream, the blades 20 are retained axially by contact with pressure between portions 28 in relief in the form of studs formed on the bottom faces of the platforms 24 and abutments or stops 18 in the form of studs projecting from the downstream sides of the teeth 16 of the disk. The studs 28 extend circumferentially from one of the longitudinal faces of the attachment members 26 and they are set back relative to the downstream side faces of the attachment members 26. Contact between the portions in relief 28 and the abutments 18 is advantageously positioned substantially level with the suction sides of the airfoils 22, beneath the feet of the airfoils. One or more portions in relief 28, e.g. two portions in relief in circumferential alignment, may be formed on the bottom face of the platform 24 of a blade 20 so as to press against an abutment 18 in the form of a stud. Likewise, a portion in relief 28 in the form of a stud made on the bottom face of the platform 24 of a blade 20 may come to press against a plurality of abutments 18 formed on a corresponding tooth 16 of the disk, e.g. two teeth 18 in circumferential alignment.
As shown in
Upstream, axial retention of the blade is provided by a plate 40. In the embodiment of
In the embodiment of
Advantageously, the plate 40 comes to press solely against the bottom portions of the teeth 16 or of the attachment members 26. The radial size of the plate 40 is thus limited, thus making it possible to avoid potential contact in operation with a stator 34 carrying the vanes 36 of a nozzle upstream from the turbine wheel.
Thus, achieving axial pressure between the blades 20 and the disk 12 and maintaining this pressure by means of the plate 40 does not give rise to encroaching on any axial clearance between the disk and a stator that is adjacent upstream or downstream, i.e. does not determine the size of said axial clearance.
Also advantageously, the retaining plate 40 presents extra thickness 41 at its periphery forming a cantilevered-out mass going away from its face pressing against the teeth 16 or the attachment members 26. This avoids the peripheral portion of the plate opening, with a loss of pressure against the teeth 16 or the attachment members 26 under the effect of the deformation induced by rotation.
In the example shown in
One or more passages or grooves constituting inspection windows 10b are advantageously formed radially in the rotor 10 so as to open out firstly in a radial face 10c of the rotor and secondly in the groove 10a. The inspection windows 10b, optionally while using an endoscope, serve to verify the proper positioning of the split ring 44.
Other ways of mounting the plate 40 on the rotor 10 with axial blocking could be adopted, e.g. a bayonet mount.
The arrangements of the axial retention means of the blades could be reversed, with abutments formed on the upstream faces of the teeth of the disk co-operating with studs formed on the platforms of the blades, and a retaining plate situated on the downstream side and exerting pressure against the downstream side faces of the teeth or attachment members of the blades.
Number | Date | Country | Kind |
---|---|---|---|
08 58689 | Dec 2008 | FR | national |
Filing Document | Filing Date | Country | Kind | 371c Date |
---|---|---|---|---|
PCT/FR2009/052553 | 12/16/2009 | WO | 00 | 6/16/2011 |
Publishing Document | Publishing Date | Country | Kind |
---|---|---|---|
WO2010/076493 | 7/8/2010 | WO | A |
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4304523 | Corsmeier et al. | Dec 1981 | A |
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5302086 | Kulesa et al. | Apr 1994 | A |
5993160 | Bouchard et al. | Nov 1999 | A |
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Number | Date | Country |
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1 498 579 | Jan 2005 | EP |
1 845 235 | Oct 2007 | EP |
2001-526345 | Dec 2001 | JP |
99 30008 | Jun 1999 | WO |
99 50534 | Oct 1999 | WO |
Entry |
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International Search Report issued May 11, 2010 in PCT/FR09/52553 filed Dec. 16, 2009. |
U.S. Appl. No. 13/139,109, filed Jun. 10, 2011, Chanteloup. |
Number | Date | Country | |
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20110250071 A1 | Oct 2011 | US |