Turbine blade

• US 5,531,568 A
• Filed: 06/05/1995
• Issued: 07/02/1996
• Est. Priority Date: 07/02/1994
• Status: Expired due to Term

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Broadhead, Peter
• Primary Examiner(s): Denion, Thomas E.
• Assistant Examiner(s): VERDIER, CHRISTOPHER M
• Application Number:
  US08/463,521
• Time in Patent Office: 393 Days
• Field of Search: 416/96 R, 416/96 A, 416/97 R, 416/97 A, 416/92, 416/189, 416/191, 416/192, 415/115, 415/116
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/186 Film cooling F01D5/187 takes precedence
• CPC Class Codes: F01D 5/225 by shrouding
• CPC Class Codes: F05D 2240/81 Cooled platforms
• CPC Class Codes: F05D 2260/2212 by creating turbulence vortex generators, turbulators or the like for mixing F05D2240/127

Abstract

A turbine blade is provided with a shroud having at least one cooling air passage extending through it. A plurality of small apertures in the passage direct cooling air as a film across the outer surface of the shroud thereby cooling it. The shroud is therefore thinner and lighter than previous shrouds which are typically provided with a large number of internal cooling air passages.

Claims

1. A turbine blade for a gas turbine engine comprising an aerofoil cross-section portion having at least one cooling air passage extending lengthwise therethrough and a shroud located at one end thereof, said shroud having at least one cooling air passage therein which is in flow communication with said at least one lengthwise extending cooling air passage in said aerofoil cross-section portion and is apertured to exhaust cooling air therefrom as a film across that part of the exterior surface of said shroud which is remote from said aerofoil cross-section portion, said at least one cooling air passage being so disposed as to be generally circumferentially extending when said blade is mounted with a plurality of similar turbine blades in an annular array, said part of the exterior surface of said shroud across which said film of cooling air flows being configured so as to enhance the heat exchange relationship between said cooling air and said shroud.

2. A turbine blade as claimed in claim 1 wherein said part of the exterior surface of said shroud is so configured by the presence of a plurality of flow disturbing ribs thereon.

3. A turbine blade for a gas turbine engine comprising an aerofoil cross-section portion having at least one cooling air passage extending lengthwise therethrough and a shroud located at one end thereof, said shroud having at least one cooling air passage therein which is in flow communication with said at least one lengthwise extending cooling air passage in said aerofoil cross-section portion and is apertured to exhaust cooling air therefrom as a film across that part of the exterior surface of said shroud which is remote from said aerofoil cross-section portion, said at least one cooling air passage being so disposed as to be generally circumferentially extending when said blade is mounted with a plurality of similar turbine blades in an annular array, said shroud being provided with a step on that part of the exterior surface thereof which is remote from said aerofoil cross-section portion and which defines a surface generally normal to said exterior surface part, said step being positioned adjacent said at least one cooling air passage within said shroud so that the apertures in said at least one cooling air passage terminate at said step on said surface thereof which is generally normal to said exterior shroud surface part.

4. A turbine blade as claimed in claim 3 wherein said apertures are of similar circular cross-section.

5. A turbine blade for a gas turbine engine comprising an aerofoil cross-section portion having at least one cooling air passage extending lengthwise therethrough and a shroud located at one end thereof, said shroud having at least one cooling air passage therein which is in flow communication with said at least one lengthwise extending cooling air passage in said aerofoil cross-section portion and is aperture to exhaust cooling air therefrom as a film across that part of the exterior surface of said shroud which is remote from said aerofoil cross-section portion, said at least one cooling air passage being so disposed as to be generally circumferentially extending when said blade is mounted with a plurality of similar turbine blades in an annular array, fences being provided on said shroud exterior surface to direct said film of cooling air in such a direction as to operationally assist in the rotation of said turbine blades.

6. A turbine blade as claimed in claim 5 wherein said at least one cooling air passage in said shroud is open ended so as to be in flow communication with the similar cooling air passage of circumferentially adjacent turbine blades when mounted on a common disc.