Compartmentalization of cooling air flow in a structure comprising a CMC component

Patent metadata

Field	Value
Publication number	US-9556750-B2
Application number	US-201314142417-A
Country	US
Kind code	B2
Filing date	Dec 27, 2013
Priority date	Mar 4, 2013
Publication date	Jan 31, 2017
Grant date	Jan 31, 2017

Abstract

A structure in a gas turbine engine comprises a spar and a CMC component adjoining the spar and separated from the spar by a cavity supplied by cooling air. At least one rope seal is installed in the cavity within a groove made in the spar to thus compartmentalize the cavity and control the flow of cooling air.

First claim

What is claimed is:

1. A gas turbine engine structure comprising:
a static metal component;
a CMC component spaced apart from the static metal component and separated therefrom by a cavity having sections with respective passages for receiving cooling air into the cavity through the static metal component and removing cooling air from the cavity through the CMC component; and
at least one rope seal located between the static metal component and the CMC component,
the rope seal dividing the cavity into the sections to thereby compartmentalize the cavity and cooling air flow is ensured.

2. The structure as claimed in claim 1 , wherein the at least one rope seal is pressed into a moon-shaped groove formed in the static metal component.

3. The structure as claimed in claim 1 , wherein the at least one rope seal is pressed into a groove formed between two raised landings with curved sidewalls extending from the static metal component.

4. The structure as claimed in claim 1 , wherein the seal is made with a single rope.

5. The structure as claimed in claim 1 , wherein the seal is made with multiple ropes dividing the cavity into a plurality of sections.

6. The structure as claimed in claim 1 , wherein the rope seal is made of a thermo stable material that includes at least one of aluminosilicate or aluminum oxide.

7. The structure as claimed in claim 1 , wherein the static metal component includes a vane spar.

8. The structure as claimed in claim 1 , wherein the static metal component includes a flow path wall above rotating blades.

9. The structure as claimed in claim 1 , wherein the static metal component includes a combustor liner.

10. A method of compartmentalizing cooling airflow in a gas turbine engine structure, the method comprising the steps of:
providing a static metal component including a spar;
providing a CMC component adjoining the spar and separated therefrom by a cavity carrying the cooling airflow; and
dividing the cavity into at least two sections by installing a rope seal between the spar and CMC component, to thereby control the flow of the cooling air in the sections of the cavity along respective passages that receive the cooling airflow into the cavity through the static metal component and remove the cooling airflow from the cavity through the CMC component.

11. The method as claimed in claim 10 , wherein dividing the cavity into at least two sections includes dividing the cavity into a plurality of sections by installing multiple rope seals.

12. The method as claimed in claim 10 , wherein the at least one impingement hole is formed in each section of the spar to receive cooling air into the section; and
wherein the at least one exit hole is formed in each section of the CMC component to remove cooling air and thereby control the flow of the cooling air in the structure.

13. The method as claimed in claim 10 , wherein the rope seal is made of thermo stable material that includes at least one of aluminosilicate or aluminum oxide.

14. A method of manufacturing a gas turbine engine structure, the method comprising the steps of:
providing a static metal component including a spar;
providing a CMC component adjacent to the spar and separated therefrom by a cavity;
installing at least one rope seal between the spar and CMC component, to thereby compartmentalize the cavity into sections;
forming at least one impingement hole in each section of the spar to receive cooling air along respective passages of the sections; and
forming at least one hole in each section of the CMC component to remove cooling air from the cavity and thereby control the flow of the cooling air in the structure.

15. The method as claimed in claim 14 , wherein installing at least one rope seal includes installing multiple rope seals to thereby divide the cavity into a plurality of sections.

16. The method as claimed in claim 14 , further comprising forming a moon-shaped groove in the spar to accommodate the at least one rope seal.

17. The method as claimed in claim 14 , further comprising forming raised landings with curved sidewalls extending from the spar to form a groove to accommodate the at least one rope seal.

18. The method as claimed in claim 14 , wherein the rope seal is made of thermo stable material that includes at least one of aluminosilicate or aluminum oxide.

19. The method as claimed in claim 18 , wherein the thermo stable material further includes aluminosilicate.

20. The method as claimed in claim 18 , wherein the thermo stable material further includes aluminum oxide.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Corp

Inventors

• Freeman Ted J
• Thomas David J

Classifications

• F01D5/189 Primary

  the insert having a tubular cross-section, e.g. airfoil shape · CPC title

• F01D5/284

  Selection of ceramic materials · CPC title

• F01D5/282

  Selecting composite materials, e.g. blades with reinforcing filaments · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2260/201

  by impingement of a fluid · CPC title