Gas turbine engine

Abstract

A blade or a vane for a gas turbine engine. The blade or vane having an aerofoil and a leading edge member attached to the aerofoil. The leading edge has an electrically conductive support member and a nano-coating formed on the support member.

Claims

1. A blade or a vane for a gas turbine engine, the blade or vane comprising: an aerofoil; and a leading edge member attached to the aerofoil; wherein the leading edge member comprises a plurality of electrically conductive support members and a nano-crystalline metallic layer formed on the plurality of electrically conductive support members, wherein the leading edge member defines a general shape of a leading edge of the blade or vane, and the aerofoil defines a general shape of a remainder of the blade or vane, wherein the nano-crystalline metallic layer extends from a forward portion of the leading edge member to form first and second wings, the first wing extending a greater distance from the leading edge member toward a trailing edge of the aerofoil than does the second wing, and wherein each electrically conductive support member of the plurality of electrically conductive support members has a surface coated with the nano-crystalline metallic layer, the plurality of electrically conductive support members arranged to be stacked in a chordwise or in a spanwise direction.

2. The blade or vane according to claim 1, wherein the nano-crystalline metallic layer comprises a Nickel-Cobalt alloy, Nickel or a Nickel alloy, and/or Cobalt or a Cobalt alloy.

3. The blade or vane according to claim 1, wherein the front portion of the leading edge member comprises the plurality of electrically conductive support members.

4. The blade or vane according to claim 1, wherein the first and second wings are bonded to the aerofoil.

5. The blade or vane according to claim 1, wherein the plurality of electrically conductive support members are arranged to be stacked in a chordwise direction.

6. The blade or vane according to claim 1, wherein the plurality of electrically conductive support members are arranged to be stacked in a spanwise direction.

7. The blade or vane according to claim 1, wherein the plurality of electrically conductive support members are made from a metallic or a polymeric material treated to be conductive.

8. The blade or vane according to claim 1, wherein the plurality of electrically conductive support members define a curved leading edge on which the nano-crystalline metallic layer is provided.

9. A method of manufacturing a blade or vane, the method comprising: providing an aerofoil body; providing a plurality of electrically conductive support members each having a surface coated with a nano-crystalline metallic layer, wherein the plurality of electrically conductive support members are arranged to be stacked in a chordwise or in a spanwise direction; electroplating the plurality of electrically conductive support members to form a leading edge member; and bonding the leading edge member to the aerofoil body.

10. The method according to claim 9, further comprising providing a tool and removably fixing the plurality of electrically conductive support member to the tool; electroplating the plurality of electrically conductive support member and the tool; and once the plurality of electrically conductive support member and the tool have been electroplated, removing the tool.

11. The method according to claim 10, wherein the leading edge member comprises a front portion and wings, and wherein the wings are formed by electroplating the tool.

12. A gas turbine engine comprising a blade or a vane according to claim 1.

13. A blade or a vane for a gas turbine engine, the blade or vane comprising: an aerofoil; and a leading edge member attached to the aerofoil; wherein the leading edge member comprises a plurality of electrically conductive support members and a nano-crystalline metallic layer formed on the plurality of electrically conductive support members, wherein each of the plurality of electrically conductive support members has a surface coated with the nano-crystalline metallic layer, and wherein the plurality of electrically conductive support members are arranged to be stacked in a chordwise or a spanwise direction.

14. The blade or vane according to claim 13, wherein the plurality of electrically conductive support members are arranged to be stacked in a chordwise direction.

15. The blade or vane according to claim 13, wherein the plurality of electrically conductive support members are arranged to be stacked in a spanwise direction.

Description

DESCRIPTION OF THE DRAWINGS

(1) Embodiments will now be described by way of example only, with reference to the Figures, in which:

(2) FIG. 1 is a sectional side view of a gas turbine engine;

(3) FIG. 2 is a side view of a blade with a leading edge member;

(4) FIG. 3 is a sectional view of the blade of FIG. 2 along the line A-A in FIG. 2;

(5) FIG. 4 is a sectional view of the leading edge member of the blade of FIG. 3 on a tool;

(6) FIG. 5 is a sectional view of an alternative leading edge member; and

(7) FIG. 6 is a sectional side view of a further alternative leading edge member.

DETAILED DESCRIPTION

(8) With reference to FIG. 1, a gas turbine engine is generally indicated at 10, having a principal and rotational axis 11. The engine 10 comprises, in axial flow series, an air intake 12, a propulsive fan 13, an intermediate pressure compressor 14, a high-pressure compressor 15, combustion equipment 16, a high-pressure turbine 17, an intermediate pressure turbine 18, a low-pressure turbine 19 and an exhaust nozzle 20. A nacelle 21 generally surrounds the engine 10 and defines both the intake 12 and the exhaust nozzle 20.

(9) The gas turbine engine 10 works in the conventional manner so that air entering the intake 12 is accelerated by the fan 13 to produce two air flows: a first air flow into the intermediate pressure compressor 14 and a second air flow which passes through a bypass duct 22 to provide propulsive thrust. The intermediate pressure compressor 14 compresses the air flow directed into it before delivering that air to the high pressure compressor 15 where further compression takes place.

(10) The compressed air exhausted from the high-pressure compressor 15 is directed into the combustion equipment 16 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 17, 18, 19 before being exhausted through the nozzle 20 to provide additional propulsive thrust. The high 17, intermediate 18 and low 19 pressure turbines drive respectively the high pressure compressor 15, intermediate pressure compressor 14 and fan 13, each by suitable interconnecting shaft.

(11) Other gas turbine engines to which the present disclosure may be applied may have alternative configurations. By way of example such engines may have an alternative number of interconnecting shafts (e.g. two) and/or an alternative number of compressors and/or turbines. Further the engine may comprise a gearbox provided in the drive train from a turbine to a compressor and/or fan.

(12) In a gas turbine engine there are a plurality of blade and vanes, for example the blades 24 of the fan 13, the blades 26, 28 of the compressors 14, 15, the blades 30, 32, 34 of the turbines 17, 18, 19, the outlet guide vanes 36 and the stator vanes 36, 40 of the compressors 14, 15.

(13) An example of a fan blade is indicated generally at 42 in FIG. 2. The fan blade includes an aerofoil portion, the aerofoil portion is made from composite material (e.g. comprises carbon fibre embedded in an epoxy resin). In alternative embodiments, the aerofoil may be made from a metallic material, e.g. from an aluminium alloy. In further alternative embodiments, the aerofoil may be made from a hybrid composite or a metal matrix composite (MMC), e.g. an aluminium MMC. The aerofoil portion defines a trailing edge 46 of the blade, a tip 52 of the blade, and a root 50 of the blade. The aerofoil portion also has a leading end 48 which is protected by a leading edge member 54. The leading edge member defines a leading edge 51 of the blade. The aerofoil portion may include a recessed region for accommodating the leading edge member creating a substantially smooth transition between the leading edge member and the aerofoil on the gas washed surface of the blade.

(14) In the present application, a chordwise direction refers to a direction extending from a leading edge 51 to a trailing edge 46 and a spanwise direction refers to a direction extending from the root 50 of the blade to the tip 52 of the blade. As is conventional, leading and trailing edges and ends are defined with respect to the axial air flow through the gas turbine engine.

(15) Referring now to FIG. 3, the leading edge member 54 includes a forward portion and two wings 58. The forward portion is adjacent the leading edge 48 of the aerofoil 44 and one wing 58 extends along and covers a portion of a suction surface 57 of the aerofoil, and the other wing 58 extends along and covers a portion of a pressure surface 59 of the aerofoil.

(16) The forward portion includes a support member 56. In the present example, the support member extends in a spanwise direction along substantially the full length of the leading edge member 54. A trailing end face of the support member contacts, e.g. abuts, the leading end 48 of the aerofoil 44. The support member is narrower at its leading end than at its trailing end, so as to complete the aerofoil shape of the blade. The support member is electrically conductive. For example, the support member may be made from a metallic alloy (e.g. a nickel, steel, titanium, or tungsten alloy), or the support member may be made from a polymeric material treated so that it conducts electricity (e.g. using embedded carbon nanotubes).

(17) The forward portion also includes a layer of nano-coating 53, which in this example is a nano-crystalline metallic layer. The nano-coating forms a skin of the leading edge member 54 and extends from the forward portion to form the wings 58. The nano-coating defines the entire gas washed surface of the leading edge member. The nano-coating in this example is a Nickel-Cobalt nano-coating, but in alternative embodiments it may be an alternative nano-coating, for example a nickel nano-coating or a cobalt nano-coating.

(18) The leading edge member 54 is attached to the aerofoil. In the present application this is achieved by bonding (e.g. using adhesive 55) the wings 58 of the leading edge member to the aerofoil 44. In the present example, the support member is not bonded directly to the aerofoil, but in alternative embodiments the support member may be bonded to the aerofoil in addition to the wings.

(19) The wings 58 of the leading edge member 54 will vary in size depending on the requirements of the blade and the dimensions of the blade. In particular, to achieve a desirable bond area between the leading edge member and the aerofoil 44, and to position the edge of a bond line between the aerofoil and the leading edge member away from peak stress locations on the aerofoil. In the present example, the wings 58 extend a different distance along the suction surface than along the pressure surface. However, in alternative embodiments, the length of the wings of the leading edge member may be the same on the pressure side of the blade and the suction side of the blade; and/or the length of the wings may vary in a spanwise direction along the blade. For example, the wings may be longest in a region where bird strike loads are expected to be greatest and where the threat of foreign object damage is most severe, e.g. at the tip of the blade.

(20) Referring to FIGS. 3 and 4, to manufacture the blade 42 shown in FIGS. 2 and 3, the support member 56 is provided. The support member is then temporarily (e.g. removably) fixed to a tool 60. Examples of how to temporarily fix the support to the tool include: the tool optionally having fixtures to clamp the tool and support member together; additionally or alternatively, pins or screws may be used; and further additionally or alternatively, a thermoplastic adhesive may be used and the assembly may be heated to remove the support member from the tool.

(21) The tool and the support member are then placed in an ion bath for electroplating. The tool and support member are connected to an electrical source and electrical current is passed through the tool and support member. This causes the nano-coating to be electroplated onto the surface of the support member and the tool. Once a desired thickness of coating is applied to the support member and the tool, the electricity supply is disconnected and the support member and tool are removed from the bath. The support member and tool can be progressively extracted from the bath to allow for a different thickness of skin (or nano-coating) to be formed at different radial locations.

(22) Next, the support member together with the nano-coating is removed from the tool, leaving the forward portion (including the support member 56 and the nano-coating 53) and the wings 58 of the leading edge member 54.

(23) An aerofoil 44 made from a suitable material, in this case a carbon fibre resin matrix composite material, is provided. The leading edge member 54 is attached to the aerofoil. In this example the wings 58 are bonded to the aerofoil 44 using an adhesive 55.

(24) With reference to FIG. 5, an alternative leading edge member 154 will be described. Similar features are given similar reference numerals but with a prefix 1 to distinguish between embodiments. Only the differences between the embodiment of FIG. 4 and the embodiment of FIGS. 2 and 3 will be described.

(25) The leading edge member 154 includes multiple support members 156a, 156b, 156c, and 156d. The support members are stacked in a chordwise direction. A nano-coating 153, in this example a nano-crystalline metallic layer, is provided on the support member nearest the leading edge and this extends to form wings 158. Each support member has a nano-coating. The support members having a leading edge surface internal to the leading edge member have a nano-coating 162a, 162b, 162c that is internal to the leading edge member.

(26) The support members 156b, 156c and 156d may be selected to be made from a material that is easier to machine than the nano-coating. In such examples, if a region of the leading edge member becomes damaged, the nano-coating and support member in that region can be removed to expose a nano-coating that was previously internal to the leading edge member. In this way, blades can be more easily re-profiled to repair damage.

(27) A further alternative embodiment is shown in FIG. 6, similar reference numerals are used as for the embodiment of FIGS. 2 and 3, but with a prefix 2. Only the differences between the embodiments will be described.

(28) The leading edge member 254 shown in FIG. 6 includes a plurality of support members 256a, 256b, 256c, 256d, 256e stacked in a radial direction (e.g. in a spanwise direction). In the present example, nano-coating 253, in this example a nano-crystalline metallic layer, is provided between the support members. The stack of support members are coated with a nano-coating, and the nano coating forms the gas washed surface of the leading edge member, including the wings 258.

(29) Providing a plurality of support members 256a, 256b, 256c, 256d and 256e stacked in a radial direction can encourage break-up of the leading edge member in the event that a fan blade is released from the fan.

(30) In further alternative embodiments the support member or support members may optionally have regions of weakness to encourage break-up of the leading edge member in the event of a fan blade being released from the fan.

(31) The leading edge member 54 and aerofoil 44 have been described with reference to a fan blade, but in alternative embodiments the leading edge member and aerofoil may form part of an alternative blade of a gas turbine engine. In further alternative embodiments the leading edge member and aerofoil may define a vane.

(32) The described embodiments provide a stator or a vane with a support member, the material of which can be varied independently of the nano-coating. The support member material can be selected to meet desired functional requirements, for example optimising for weight, cost, performance, or reduction of containment loads.

(33) The provision of a support member also means that the nano-coating can be thinner than it would need to be without the support member. This means that the time taken to manufacture the leading edge member can be reduced.

(34) As described, the provision of a support member also means that it is possible to configure the leading edge member so as to ease repair of the leading edge member. The support member can also be configured to encourage break-up of the leading edge member in the event of a fan blade being released from the fan, so as to reduce containment loads.

(35) It will be understood that the invention is not limited to the embodiments above-described and various modifications and improvements can be made without departing from the concepts described herein. Except where mutually exclusive, any of the features may be employed separately or in combination with any other features and the disclosure extends to and includes all combinations and sub-combinations of one or more features described herein.