Fan

Abstract

A fan for a gas turbine engine, the fan comprising a first set of fan blades and a second set of fan blades arranged circumferentially around a hub. Each of the fan blades of the first and second set comprises an organic matrix composite body and a leading edge member connected to the body. The leading edge member of the first set of fan blades has a mass less than the leading edge member of the second set of fan blades.

Claims

1. A fan for a gas turbine engine, the fan comprising: a first set of fan blades and a second set of fan blades arranged circumferentially around a hub, each of the fan blades of the first and second set comprises an organic matrix composite body and a leading edge member connected to the body, wherein the leading edge member of the first set of fan blades has a mass less than the leading edge member of the second set of fan blades, wherein a leading edge region of the first set of fan blades and a leading edge region of the second set of fan blades have a same exterior shape, wherein the mass of a radially inner portion of the leading edge member of the blades of the first set of blades is less than the mass of a radially inner portion of the leading edge member of the blades of the second set of blades, wherein the radially inner portion extends from a mid-spanwise location to a root of the blade, and wherein the mass of the leading edge member of the second set of fan blades is increased by providing a leading edge member with a greater volume in the region of greater mass than the fan blades of the first set.

2. The fan according to claim 1, wherein the blades of the first set and of the second set have the same gas washed surface area, shape and profile.

3. The fan according to claim 1, wherein the volume of the leading edge member of the first set of fan blades is smaller than the volume of the leading edge member of the second set of fan blades.

4. The fan according to claim 1, wherein the mass of a radially outer portion of the leading edge member of the first set is the same as the mass of a radially outer portion of the leading edge member of the second set, the radially outer portion of the leading edge member extends from a mid-spanwise location of the blade to a tip of the blade.

5. The fan according to claim 1, wherein the mass of a root portion of the leading edge member of the first set is less than the mass of a root portion of the leading edge member of the blades of the second set, the root portion extending from a spanwise location that is 30% of the total span of the blade to a root of the blade.

6. The fan according to claim 1, wherein the leading edge member of the first set and the second set comprises a forward portion that defines a leading edge of the blade, a wing that extends from the forward portion along a suction side of the blade and a wing that extends from the forward portion along a pressure side of the blade, and wherein the forward portion of the first set of blades has a lower mass or volume than the forward portion of the second set of blades.

7. The fan according to claim 1, wherein the leading edge member of the first set and the second set comprises a forward portion that defines a leading edge of the blade, a wing that extends from the forward portion along a suction side of the blade and a wing that extends from the forward portion along a pressure side of the blade, and wherein the wings of the first set of blades have a lower mass or volume than the wings of the second set of blades.

8. The fan according to claim 1, wherein the leading edge member is made from a metallic material.

9. The fan according to claim 8, wherein the leading edge member is made from steel, titanium or a titanium alloy.

10. The fan according to claim 1, wherein the body is made from a carbon reinforced resin matrix material.

11. The fan according to claim 1, wherein the blades of the first set and of the second set have the same gas washed surface area, shape and profile and wherein the volume of the leading edge member of the first set of fan blades is smaller than the volume of the leading edge member of the second set of fan blades.

12. A gas turbine engine comprising the fan according to claim 1.

Description

BRIEF 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 perspective view of a fan blade;

(4) FIG. 3 is a partial cross section through a leading edge region of a fan blade of a first fan blade set;

(5) FIG. 4 is a partial cross section through a leading edge region of a fan blade of a second fan blade set;

(6) FIG. 5 is a view from the pressure side of a fan blade of a first fan blade set; and

(7) FIG. 6 is a view from the pressure side of a fan blade of a second fan blade set.

DETAILED DESCRIPTION OF THE DRAWINGS

(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) The fan 13 includes a plurality of fan blades 40 mounted circumferentially around a hub.

(13) Referring to FIG. 2, the fan blades 40 each comprise an aerofoil portion 42 having a leading edge 44, a trailing edge 46, a concave pressure surface wall 48 extending from the leading edge to the trailing edge and a convex suction surface wall extending from the leading edge to the trailing edge. The fan blade has a root 52 via which the blade can be connected to the hub. The fan blade has a tip 56 at an opposing end to the root. In the present application, a spanwise direction S refers to a direction that extends between the root of the blade and a tip of the blade; a chordwise direction C refers to a direction that extends from the leading edge of the blade to the trailing edge of the blade; and a thickness direction T refers to a direction that extends from the pressure surface of the blade to the suction surface of the blade.

(14) The fan blade includes a body 58 made from an organic matrix composite material. In this example, the organic matrix composite material is a carbon fibre reinforced resin matrix. The body may also comprise reinforcement elements, by way of example only, the reinforcement elements may be stitches, tufts or pins. A metallic leading edge member 50 and a metallic trailing edge member 54 are provided at a forward end and rearward end, respectively, of the body and connect thereto.

(15) The fan includes a first set of fan blades and a second set of fan blades. Blades of the first set and the second set are arranged around the hub of the fan, e.g. alternating or in groups of two or more. In the present example, the blades of the first set have the same aerodynamic profile as the blades of the second set.

(16) That is, they have the same gas washed surface area, same gas washed shape, and same gas washed profile (or dimensions).

(17) The difference between the first set of blades and the second set of blades is the mass of the leading edge member. The mass of the leading edge member may be altered in a number of different ways, for example the leading edge members may be made from different materials, or they may be constructed in a different manner, for example the leading edge member may include a varying number or volume of hollow regions.

(18) Referring to FIGS. 3 and 4, in the present example, the mass of the leading edge member 50a of the first set of fan blades is arranged to be less than the mass of the leading edge member 50b of the second set of fan blades by making the volume of the leading edge member 50a less than the volume of the leading edge member 50b.

(19) The leading edge members 50a, 50b include a forward portion 60a, 60b, a wing 62a, 62b that extends along a suction side of the blade, and a wing 64a, 64b that extends along a pressure side of the blade. The wings 62a, 62b, 64a, 64b extend along only a partial chordwise extent of the blade. As can be seen by comparing FIGS. 3 and 4, to reduce the volume of the leading edge member 50a of the first set of blades compared to the leading edge member 50b of the second set of blades, the forward portion 60a of the first set of blades may have a smaller volume than the forward portion 60b of the second set of blades. In this example, the forward portion 60a extends by a shorter chordal distance than the forward portion 60b. However, the overall dimensions of the blade remain the same, because the body 58a of the first set of blades is arranged to have a greater chordal extent than the body 58b of the second set of blades. In the presently described example, the chordal extent of the entire leading edge is the same for the first set of blades and the second set of blades. This is achieved because the leading edge member of the first set of blades has longer wings 62a, 64a than the leading edge member of the second set of blades 62b, 64b. The bodies 58a, 58b of the blades include recesses 61a, 63a, 61b, 63b for receiving the wings, such that a gas washed surface of the wings is substantially flush with a gas washed surface of the body.

(20) Referring to FIGS. 5 and 6, in alternative embodiments, additionally or alternatively, the wings (only one wing 162b is illustrated in FIG. 6) of the leading edge member 150b of the second set of blades may be modified, compared to the wings (only one wing 162a is illustrated in FIG. 5) of the leading edge member 150a of the first set of blades, to provided additional mass to the wings of the leading edge members of the second set of blades. In this example, the blades 140a, 140b again have the same overall dimensions and shape regardless of whether they are in the first set of fan blades or the second set of fan blades, but the body 158b of the second set of blades has a different shape to the body 158a of the first set of blades, so as to accommodate the different wings.

(21) In this example, the leading edge member 150b is larger in a radially inner portion 166 than a radially outer portion 168 compared to the leading edge member 150a. The radially inner portion extends from a mid-spanwise position 170 to the root 152 of the blade and the radially outer portion extends from the mid-spanwise position 170 to the tip 156 of the blade. The leading edge member is particularly larger in a root portion 172 of the blade. The root portion of the blade is proximal to and extends from the root, and has a spanwise length of approximately 30% of the full span of the blade.

(22) Provision of a first set of blades and a second set of blades, the first set of blades having a leading edge member of a different mass to the leading edge member of the second set of blades allows for mistuning. Mistuning can result in increased flutter stability. In the described examples, the size of the body is adapted to accommodate a leading edge of different dimensions which means that flutter stability can be increased without penalising aerodynamic efficiency of the blade.

(23) Arranging the leading edge members of the second set of fan blades to have increased mass near the root of the blades, means that additional material is being added in a region of the blade that in use has high strain energy and low kinetic energy, and this can further reduce flutter.

(24) As will be appreciated, the wings and/or the forward portion may be arranged to be larger in a region proximal to the blade root.

(25) Two different sets of fan blades have been described, but in alternative embodiments further different sets of fan blades may be provided.

(26) 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.