Aerofoil
Composite aerofoils for gas turbine engines are commonly provided with a metal protection strip along the leading edge, to prevent erosion of the leading edge in use and to protect against impacts from foreign bodies. A problem with such strips is that they can cause serious damage to other parts of the engine if they become detached from the aerofoil. The invention provides an aerofoil having such a protection strip, characterized in that the protection strip includes one or more weakening features to reduce the ability of the protection member to withstand a compressive force applied along its length. The weakening features encourage the protection member to break up under impact, or if it becomes detached from the aerofoil, so that damage to other parts of the engine is minimized.
1. An aerofoil for a gas turbine engine, the aerofoil comprising:
a body and
a protection member, the protection member extending along a length of the aerofoil body, the protection member including:
a protection member body;
a pair of spaced wings extending outwardly from the protection member body, the pair of spaced wings defining an aerofoil body receiving recess therebetween; and
a stiffening member extending between the pair of spaced wings and extending along a length of the protection member, the stiffening member having a plurality of apertures therethrough, wherein
a part of the aerofoil body protrudes through the plurality of apertures into the aerofoil body receiving recess.
2. The aerofoil according to claim 1 , in which the stiffening member is in a form of a web.
3. The aerofoil according to claim 1 , in which
the aerofoil body includes an interlocking formation to provide interlock between the aerofoil body and the protection member.
4. The aerofoil according to claim 1 , in which
the aerofoil includes a filler, which is located in a cavity defined between the aerofoil body and the protection member.
5. The aerofoil according to claim 4 , in which
the filler acts to dampen vibrations.
6. The aerofoil according to claim 1 , in which
the protection member is formed of a metallic material, and
the aerofoil body is formed of a composite material.
7. A gas turbine engine including
the aerofoil according to claim 1 .
8. The aerofoil according to claim 1 , wherein
the protection member defines a weakening feature which is arranged, in use, to reduce an ability of the protection member to withstand a compressive force applied along a length of the protection member.
9. A method of forming an aerofoil, the aerofoil comprising: an aerofoil body, the aerofoil body being formed of a composite material, and a protection member, the protection member being formed of a metallic material, the protection member including: a protection member body, and a pair of spaced wings extending outwardly from the protection member body, the pair of spaced wings defining an aerofoil body receiving recess therebetween; a stiffening member extending between the pair of spaced wings and extending along a length of the protection member, the stiffening member having a plurality of apertures therethrough; the method including the steps of
locating the protection member in a mould, and
then locating the composite material in the mould to form the aerofoil body against the protection member so that a part of the aerofoil body protrudes through the plurality of apertures into the aerofoil body receiving recess.
10. The aerofoil according to claim 8 , wherein
the weakening feature extends transversely across the length of the protection member.
11. The aerofoil according to claim 8 , in which
the protection member includes a plurality of weakening features.