초록 ▼

An aerofoil 20 for a gas turbine engine includes a root portion 22, a tip portion 24 located radially outwardly of the root portion 22, leading and trailing edges 26, 28 extending between the root portion 22 and the tip portion 24 and an internal cooling passage 34. The aerofoil 20 includes a plural

An aerofoil 20 for a gas turbine engine includes a root portion 22, a tip portion 24 located radially outwardly of the root portion 22, leading and trailing edges 26, 28 extending between the root portion 22 and the tip portion 24 and an internal cooling passage 34. The aerofoil 20 includes a plurality of cooling fluid discharge apertures 36 extending between the root portion 22 and the tip portion 24 in a trailing edge region 28a to discharge cooling fluid from the internal cooling passage 34 to an outer surface 31 of the aerofoil in the trailing edge region 28a and thereby provide a cooling film in the trailing edge region 28a. The cooling fluid discharge apertures 36 are arranged so that the flow rate of the cooling fluid discharged from the internal cooling passage 34 to the outer surface trailing edge region 28a varies between the root portion 22 and the tip portion 24.

대표청구항 ▼

The invention claimed is: 1. An aerofoil comprising: a root portion; a tip portion located radially outwardly of the root portion; leading and trailing edges extending between the root portion and the tip portion; an internal cooling passage; and a plurality of cooling fluid discharge apertures ext

The invention claimed is: 1. An aerofoil comprising: a root portion; a tip portion located radially outwardly of the root portion; leading and trailing edges extending between the root portion and the tip portion; an internal cooling passage; and a plurality of cooling fluid discharge apertures extending between the root portion and the tip portion in a trailing edge region to discharge cooling fluid from the internal cooling passage to an outer surface of the aerofoil in the trailing edge region during use and provide a cooling film in the trailing edge region, the plurality of cooling fluid discharge apertures comprising first, second and third apertures, a distance being defined between each aperture and the trailing edge, wherein said distance for the second aperture is less than the distance for each of the first and third apertures so that the flow rate of the cooling fluid discharged from the internal cooling passage to the outer surface trailing edge region varies between the root portion and the tip portion. 2. An aerofoil according to claim 1, wherein the distance is determined for each cooling fluid discharge aperture in order to meter the flow rate of the cooling fluid discharged to the outer surface trailing edge region between the root portion and the tip portion to maintain the trailing edge region at a substantially constant temperature between the root portion and the tip portion. 3. An aerofoil according to claim 1, wherein the cooling fluid discharge apertures are generally equispaced between the root portion and the tip portion. 4. An aerofoil according to claim 1, wherein the aerofoil includes concave and convex walls, and the cooling fluid discharge apertures are defined in or by the concave wall. 5. An aerofoil according to claim 1, wherein the aerofoil is a blade or a guide vane for a gas turbine engine. 6. A gas turbine engine including an aerofoil as defined in claim 1. 7. An aerofoil according to claim 1, wherein either the first or third aperture is adjacent the root or tip portions respectively. 8. An aerofoil according to claim 1, wherein the decrease in distance from the first or third aperture to the second aperture is a uniform amount over each adjacent aperture. 9. An aerofoil according to claim 1, wherein a cutback portion is defined in the trailing edge region and provides a shield to prevent working gas mixing with the cooling film. 10. An aerofoil according to claim 1, wherein the plurality of apertures comprises apertures of different sizes.