GAS TURBINE ENGINE COMPONENT

• US 20140093379A1
• Filed: 10/02/2013
• Published: 04/03/2014
• Est. Priority Date: 10/03/2012
• Status: Abandoned Application

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: TIBBOTT, Ian, JACKSON, Dougal Richard
• Application Number:
  US14/044,460
• Publication Number:
  US 20140093379A1
• Time in Patent Office: Days
• US Class Current: 416/224
• CPC Class Codes: B33Y 80/00 Products made by additive manufacturing
• CPC Class Codes: F01D 5/188 with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
• CPC Class Codes: F01D 5/189 the insert having a tubular cross-section, e.g. airfoil shape
• CPC Class Codes: F05D 2260/201 by impingement of a fluid
• CPC Class Codes: F05D 2260/202 by film cooling
• CPC Class Codes: F05D 2260/30 Retaining components in desired mutual position
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 29/49332 Propeller making
• CPC Class Codes: Y10T 29/49336 Blade making

Abstract

A gas turbine engine component is described which (100), comprises: a shell having an internal cavity for receiving a multi-part insert; a multi-part insert located within the cavity, wherein the multi-part insert comprises separate insert parts assembled in an abutting relation with one another within the cavity to provide the multi-part insert; an insertion aperture within a wall of the shell which is sized to receive each of the insert parts individually and wherein the multi-part insert cannot be withdrawn from the cavity through the insertion aperture when assembled.

Claims

1. A gas turbine engine component (100), comprising

a shell having an internal cavity for receiving a multi-part insert;

a multi-part insert located within the cavity, wherein the multi-part insert comprises separate insert parts assembled in an abutting relation with one another within the cavity to provide the multi-part insert;

an insertion aperture within a wall of the shell which is sized to receive each of the insert parts individually and wherein the multi-part insert cannot be withdrawn from the cavity through the insertion aperture when assembled.

2. A gas turbine component as claimed in claim 1, wherein the cavity includes an insertion portion into which the insert parts are inserted, and a receiving portion in which at least one of the insert parts is located when the insert is assembled.

3. A gas turbine component as claimed in claim 2, wherein the receiving portion is at least partially obscured by a wall or an internal protuberant feature of the shell when viewed from the insertion aperture.

4. A gas turbine component as claimed in claim 3, wherein the obstruction of the receiving portion is caused by a twist along the length of the cavity.

5. A gas turbine component as claimed in claim 3, wherein the cavity includes a widened portion along the length thereof and the receiving portion may be located within the widened portion of the cavity.

6. A gas turbine engine as claimed in claim 1 where the assembled insert includes at least one retention part, wherein the retention part acts to engage with a portion of the cavity and the at least one other insert part so as to retain the assembled insert within the cavity.

7. A gas turbine component as claimed in claim 1, wherein the retention part provides a resilient bias which acts to urge the retention part and or another insert part against one or more walls of the shell.

8. A gas turbine component as claimed in claim 1, wherein the retention part may be oversized relative to the size required when in situ such that inserting the retention part into the cavity requires a deformation of the part and a resulting stressing to provide the bias.

9. A gas turbine component as claimed in claim 1, wherein at least one insert piece is made by additive layer manufacturing;

and

wherein the insert includes formations which support the insert within the shell and guide the cooling air around the inner surface of the shell.

10. A gas turbine engine component as claimed in claim 1, wherein the shell is a ceramic matrix composite shell.

11. A gas turbine engine component as claimed in claim 1, wherein the formations include projections.

12. A gas turbine engine component according to claim 1, wherein at least one of the insert parts predominantly includes trip strip formations which lie along the inner surface of the shell when the insert is assembled.

13. A gas turbine engine component as claimed in claim 1, wherein the shell forms an aerofoil and includes a wall which divides the shell into a front cavity at a leading edge region of the component and a rear cavity at a trailing edge region of the component;

and wherein the multi-part insert is located in the front cavity or a rear insert located in the rear cavity.

14. A gas turbine engine component as claimed in claim 13, wherein the divider wall includes apertures which provide fluid communication between the front and rear cavity, and at least one part of the multiple insert parts includes a sealing plate to restrict or prevent the flow of cooling air across the divider wall.

15. A method of forming the gas turbine engine component according to claim 1, the method including the steps of:

providing the shell;

providing a plurality of insert parts which are configured to be assembled in an abutting relation with one another within the cavity to provide the multi-part insert;

wherein the assembled insert includes at least one retention part which engages with a wall of the cavity and at least one other insert part so as to retain the assembled insert within the cavity.