Turbine blade and manufacture thereof

• US 6,358,013 B1
• Filed: 09/26/2000
• Issued: 03/19/2002
• Est. Priority Date: 10/12/1999
• Status: Expired due to Term

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Rose, Martin G, Dodd, Alec G
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): Kershteyn, Igor
• Application Number:
  US09/669,719
• Time in Patent Office: 539 Days
• Field of Search: 416/224, 416/229.A, 416/230, 416/241.B, 415/914
• US Class Current: 416/229.00A
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F01D 5/147 Construction, i.e. structural features, e.g. of weight-saving hollow blades F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18
• CPC Class Codes: Y10S 415/914 Device to control boundary layer

Abstract

A gas turbine blade (10) which has a rounded trailing edge (18), is provided with a row of side by side arranged ceramic fibres (20) along the trailing edge (18). During operation of the turbine blade (10), the rounded shape of trailing edge (18) causes gasflows to break from the rounded edge before reaching the edge extremity. The presence of the fibres (20) prevent the formation of vortices in the gasflow, and thereby improve turbine efficiency.

Claims

1. A gas turbine engine turbine blade comprising an aerofoil having a trailing edge, from the end extremity of which trailing edge which there projects a plurality of elongate ceramic fibres, in a direction parallel with the mean direction of gasflows which leave said trailing edge during operation of said turbine blade in an associated gas turbine engine, said fibres being arranged in side by side relationship along at least a substantial portion of said trailing edge extremity.

2. A gas turbine engine turbine blade as claimed in claim 1 wherein a slot is formed in the length of the extremity of the trailing edge thereof, said ceramic fibres being directly located in said slot.

3. A gas turbine engine turbine blade as claimed in claim 1 wherein a slot is formed in the length of the extremity of said trailing edge of said blade, said ceramic fibres being located in a folded strip of material, said strip being located in said slot.

4. A gas turbine engine turbine blade as claimed in claim 1 wherein said ceramic fibres are silicon carbide fibres.

5. A gas turbine engine turbine blade as claimed in claim 3 wherein the material from which said strip is made, is selected from the group consisting of:

N75;

N80 and Haynes 25.

6. A method of fixing a plurality of ceramic fibres into the trailing edge portion of a gas turbine engine turbine blade so as to protrude therefrom in a direction parallel with the mean direction of gasflows which leave said trailing edge of said turbine blade during operation in a gas turbine engine, comprising the steps of forming a slot in the blade trailing edge extremity, along at least a major portion of the trailing edge length, arranging a plurality of ceramic fibres in side by side relationship, directly or indirectly in said slot, and then squeezing the sides of said slot towards each other, so as to, directly or indirectly trap and retain said ceramic fibres in the trailing edge portion of said turbine blade.

7. A method of fixing a plurality of ceramic fibres into the trailing edge portion of a turbine blade as claimed in claim 6, wherein said ceramic fibres are arranged directly in said slot in said trailing edge, and the sides of said slot squeezed towards each other, so as to trap and retain said ceramic fibres therein.

8. A method of fixing a plurality of ceramic fibres into the trailing edge portion of a turbine blade as claimed in claim 7, including proportioning the dimensions of both slot and ceramic fibres, such that said slot sides provide sufficient grip thereon if squeezed up to 0.5% of the normally allowed movement to correct the blade shape.

9. A method of fixing a plurality of ceramic fibres into the trailing edge portion of a turbine blade as claimed in claim 6, wherein a strip of material which is compatible with the material from which said blade is made, is folded along its length to form opposing walls, between which said walls said ceramic fibres are then arranged in side by side relationship, and the walls thereafter squeezed, so as to trap and retain said ceramic fibres therein, and wherein a slot is formed in the trailing edge of said blade, for the receipt and gripping of said strip, by squeezing the sides of said slot towards each other.

10. A method of fixing a plurality of ceramic fibres into the trailing edge of a turbine blade as claimed in claim 9, including proportioning the dimensions of the blade slot and folded, squeezed strip, such that said blade slot sides provide sufficient grip thereon, if squeezed up to 0.5% of the normally allowed movement to correct the blade shape.