The present invention relates to a gas turbine engine component with an abrasive coating.
Gas turbine engines have turbine rotor blades which rotate relative to a surrounding casing. To reduce heat generation, protect the blade and to form a seal between the blade and the casing, an abrasive coating may be attached to the blade tip. For example,
When attaching the abrasive coating, the hard particles may be tacked to the blade tip to hold them in place before the matrix is applied. Near to the edge of the blade tip, these tacked hard particles may drop off. This is particularly problematic when an abrasive coating is applied to a narrow section. For example,
A further problem arises if hard particles located at an edge encourage matrix material to be laid down overhanging the edge. Such overhangs can increase aerodynamic losses and may interfere with blade film cooling in the adjacent aerofoil surface.
Moreover, the abrasive coating on both the smooth and the squealer tipped blades is generally attached to a smooth surface. At elevated temperatures under near plastic conditions, the strength of the coating or the strength of the attachment between the coating and smooth surface may be insufficient to prevent the coating from being smeared off.
The present invention aims to provide a gas turbine engine component with an abrasive coating which can reduce aerodynamic loses, decrease interference with component cooling systems, and improve the attachment of the coating to the component.
Accordingly, in a first aspect, the present invention provides a gas turbine engine component having:
In a second aspect, the present invention provides a gas turbine engine having a component according to any one of the previous claims.
Optional features of the invention will now be set out. These are applicable singly or in any combination with any aspect of the invention.
The hard particles may be cubic boron nitride particles.
The matrix may be nickel, cobalt, iron or an alloy of any one or more thereof.
The hard particles may project beyond the raised rim, such that, in use, the hard particles abrade a runner surface of an adjacent component.
The component may be made of a nickel-based superalloy, steel or titanium-based alloy.
The retaining matrix may be electroplated.
The component may be a rotor blade. For example, the component may be a turbine blade, a compressor blade or a fan blade. The hard particles can then project radially beyond the raised rim, such that, in use, the hard particles abrade a runner surface of a casing surrounding the rotor blade. The blade may be squealer tipped or smooth tipped.
The component may have one or more seal fins, the or each seal fin having the raised rim and the abrasive coating at a tip region thereof. The one or more seal fins may form part of a labyrinth seal.
The raised rim may be produced by casting, electro-discharge machining, milling or additive layer manufacture. For example, the rim may be produced by laser cladding.
The raised rim may have a height of approximately 0.15 mm. The hard particles may have a mean diameter of between 0.18 and 0.25 mm.
Embodiments of the invention will now be described by way of example with reference to the accompanying drawings in which:
With reference to
During operation, air entering the intake 11 is accelerated by the fan 12 to produce two air flows: a first air flow A into the intermediate-pressure compressor 13 and a second air flow B which passes through the bypass duct 22 to provide propulsive thrust. The intermediate-pressure compressor 13 compresses the air flow A directed into it before delivering that air to the high-pressure compressor 14 where further compression takes place.
The compressed air exhausted from the high-pressure compressor 14 is directed into the combustion equipment 15 where it is mixed with fuel and the mixture combusted. The resultant hot combustion products then expand through, and thereby drive the high, intermediate and low-pressure turbines 16, 17, 18 before being exhausted through the nozzle 19 to provide additional propulsive thrust. The high, intermediate and low-pressure turbines respectively drive the high and intermediate-pressure compressors 14, 13 and the fan 12 by suitable interconnecting shafts.
The engine 10 contains turbine blades, and the tips of these blades may be coated in an abrasive coating according to the present invention, as shown in the schematic cross section through an abrasive tipped turbine blade of
The turbine blade 1 has a raised rim 9 located along the outer edges of the tip of the blade. The rim bounds an inner area of the tip region on which is formed an abrasive coating 3 including hard particles 5 of cubic boron nitride embedded in a retaining matrix 7 of nickel. The raised rim has a height in a span direction of approximately 0.15 mm. Advantageously, the rim helps to anchor the coating on the tip, provides resistance to plastic deformation of the matrix, and reduces the likelihood of the abrasive coating being smeared off from the blade when in use. Also, during production, the rim corrals the particles, providing a stop and support to prevent particles being located near an outer edge of the blade tip, and either falling off or causing an unwanted build-up of retaining matrix along the outer edges. Thus, the rim can improve the aerodynamics of the coated blade and reduce any negative impact of the coating on the blade's film cooling system.
The hard particles 5 typically have a mean diameter of between 0.18 and 0.25 mm. Consequently, the raised rim has a height of between 50% and 75% of the mean diameter of the hard particles 5. In the abrasive coating 3, the hard particles 5 are located such that they project beyond the raised rim and in use, abrade a runner surface of a casing surrounding the blade. To prevent the particles falling out, they are held in place by the matrix 7, which can be applied by electroplating. For example, Praxair Surface Technologies TBT406™ electroplating process or Abrasive Technologies ATA3C™ electroplating process may be used. In such processes, an electroplated entrapment layer entraps undersides of the abrasive particles to hold them in position on the blade, and then the retaining matrix is electroplated to complete the coating. However, alternative matrix materials, such as cobalt, iron or an alloy of any one or more thereof, and alternative methods of attachment may be used. For example, the matrix could comprise NiCoCrAlY.
As shown in
The raised rims can be produced by casting, electro-discharge machining, milling or an additive layer manufacturing process such as laser cladding.
While the invention has been described in conjunction with the exemplary embodiments described above, many equivalent modifications and variations will be apparent to those skilled in the art when given this disclosure. Thus, the invention is not limited to turbine blade applications but may be used for other applications. For example, in a gas turbine engine context, the abrasive coating can be usefully applied to the tips of other rotor blades such as compressor blades or fan blades such that the coating abrades a runner surface of a surrounding casing. As another example, the abrasive coating may be applied to the tips of seal fins located on a gas turbine engine component, the abrasive coating thereby enhancing the ability of the fins to abrade a facing runner surface. In the case of seal fins, the fins may form part of a labyrinth seal, wherein the resistance to airflow is created by forcing the air to traverse through a series of fins. Accordingly, the exemplary embodiments of the invention set forth above are considered to be illustrative and not limiting. Various changes to the described embodiments may be made without departing from the spirit and scope of the invention.
Number | Date | Country | Kind |
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1508637.4 | May 2015 | GB | national |
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Entry |
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Ameri et. al., Effect of Squealer Tip on Rotor Heat Transfer and Efficiency, ASME, Journal of Turbomachinery, vol. 120 No. 4, Oct. 1998, pp. 753-759 (provided by applicant on Mar. 14, 2019) (Year: 1998). |
Nov. 20, 2015 Search Report issued in British Patent Application No. 1508637.4. |
Oct. 12, 2016 Search Report issued in European Patent Application No. 16166361. |
Ameri et al.; “Effect of Squealer Tip on Rotor Heat Transfer and Efficiency;” Journal of Turbomachinery; Oct. 1998; vol. 120; pp. 753-759. |
Jan. 24, 2018 Office Action issued in European Patent Application No. 16166361.2. |
Number | Date | Country | |
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20160341051 A1 | Nov 2016 | US |