COOLED AEROFOIL FOR A GAS TURBINE ENGINE
First Claim
1. A cooled aerofoil for a gas turbine engine, the aerofoil having an aerofoil section with pressure and suction surfaces extending between inboard and outboard ends thereof, wherein the aerofoil section includes:
- first and second internal passages for carrying cooling air, anda plurality of holes in the external surface of the aerofoil section which receive cooling air from the internal passages, the external holes being arranged such that cooling air exiting a first portion of the external holes participates in a cooling film extending from the leading edge of the aerofoil section over said pressure surface and cooling air exiting from a second portion of the external holes participates in a cooling film extending from the leading edge over said suction surface; and
wherein the first portion of external holes receives cooling air from the first internal passage, the second portion of external holes receives cooling air from the second internal passage, and the first and second internal passage are supplied with cooling air from respective and separate passage entrances, each entrance being located at either the inboard end or the outboard end of the aerofoil section.
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Accused Products
Abstract
A cooled aerofoil for a gas turbine engine has an aerofoil section with pressure and suction surfaces extending between inboard and outboard ends thereof. The aerofoil section includes first and second internal passages for carrying cooling air. The aerofoil section further includes a plurality of holes in the external surface of the aerofoil section which receive cooling air from the internal passages. The external holes are arranged such that cooling air exiting a first portion of the external holes participates in a cooling film extending from the leading edge of the aerofoil section over said pressure surface and cooling air exiting from a second portion of the external holes participates in a cooling film extending from the leading edge over said suction surface. The first portion of external holes receives cooling air from the first internal passage, and the second portion of external holes receives cooling air from the second internal passage. The first and second internal passages are supplied with cooling air from respective and separate passage entrances. Each entrance is located at either the inboard end or the outboard end of the aerofoil section.
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Citations
13 Claims
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1. A cooled aerofoil for a gas turbine engine, the aerofoil having an aerofoil section with pressure and suction surfaces extending between inboard and outboard ends thereof, wherein the aerofoil section includes:
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first and second internal passages for carrying cooling air, and a plurality of holes in the external surface of the aerofoil section which receive cooling air from the internal passages, the external holes being arranged such that cooling air exiting a first portion of the external holes participates in a cooling film extending from the leading edge of the aerofoil section over said pressure surface and cooling air exiting from a second portion of the external holes participates in a cooling film extending from the leading edge over said suction surface; and wherein the first portion of external holes receives cooling air from the first internal passage, the second portion of external holes receives cooling air from the second internal passage, and the first and second internal passage are supplied with cooling air from respective and separate passage entrances, each entrance being located at either the inboard end or the outboard end of the aerofoil section. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13)
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Specification