Blade or vane for a gas turbine engine

• US 4,168,938 A
• Filed: 01/28/1977
• Issued: 09/25/1979
• Est. Priority Date: 01/29/1976
• Status: Expired due to Term

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Dodd, Alec G.
• Primary Examiner(s): Bentley, Stephen C.
• Application Number:
  US05/763,707
• Time in Patent Office: 970 Days
• Field of Search: 415/115, 416/96 R, 416/96 A, 416/97 R, 416/97 A, 60/39.66
• US Class Current: 416/97.00R
• CPC Class Codes: F01D 5/188 with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall

Abstract

A hollow blade or vane for a gas turbine engine is provided with a longitudinally extending, hollow thickened portion in its wall adjacent the leading edge. This hollow thickened portion acts as an integral strut and relieves the leading edge of some loads.

Claims

1. A hollow blade or vane for a gas turbine engine comprising a thin-walled hollow aerofoil section of generally uniform wall thickness and devoid of flank-connecting ribs adjacent the leading edge, the wall of said aerofoil section being provided with a longitudinally extending thickened portion adjacent said leading edge, the transverse dimensions of said portion being less than the thickness of said section, said thickened portion itself being hollow so that it forms an integral hollow strut in said wall to resist bending stresses in said wall adjacent said leading edge.

2. A hollow blade or vane as claimed in claim 1 and in which said hollow blade or vane comprises a platform on at least one extremity of the aerofoil, the hollow strut extending to and being connected with said platform to take the bending stresses thereto.

3. A hollow blade or vane as claimed in claim 2 and in which said hollow strut is provided with cooling air entry holes through which cooling air may flow into its hollow interior from the interior of the section.

4. A hollow blade or vane as claimed in claim 3 and in which said hollow strut is provided with cooling air exit holes adapted to allow cooling air to flow out from its hollow interior to the surface of the blade or vane to provide film cooling of the surface.

5. A hollow blade or vane as claimed in claim 1 and comprising a cooling air entry tube extending longitudinally within the hollow interior of the blade or vane and abutting against said hollow strut which acts as a location feature for the tube.

6. A hollow blade or vane as claimed in claim 5 and in which the hollow strut is provided with cooling air entry holes which communicate with the interior of the air entry tube so that cooling air may flow from the cooling air entry tube into the hollow strut.

7. A hollow blade or vane as claimed in claim 5 and in which said air entry tube comprises a plurality of apertures therein through which cooling air may flow from its interior to impingement cool the interior of the blade or vane.

8. A hollow blade or vane as claimed in claim 1 and in which the leading edge region of the blade or vane wall has holes through it through which cooling air may flow from the hollow interior of the strut to the exterior surface of the leading edge to film cool this surface.

9. A hollow blade or vane as claimed in claim 1 and comprising a transverse, longitudinally extending web which divides the hollow interior of the vane into a forward and a rearward portion.