# US 10,502,072 B2 · Compartmentalization of cooling air flow in a structure comprising a CMC component

> Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt

- Number: US 10,502,072 B2
- Document ID: US10502072B2
- Status: Granted
- Kind: B2
- Application number: 15/383,335
- Filed: 2016-12-19
- Published: 2017-10-19
- Granted: 2019-12-10
- Earliest claimed: 2013-03-04
- Assignees: Rolls-Royce North American Technologies Inc.; ROLLS-ROYCE plc
- Applicants: Rolls-Royce North American Technologies, Inc.; Rolls-Royce Corporation
- Inventors: Ted J. Freeman; David J. Thomas
- Web page: https://patentgrep.com/patent/US10502072B2

## CPC

- F01D 5/189: {the insert having a tubular cross-section, e.g. airfoil shape}
- 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)}
- F01D 5/282: {Selecting composite materials, e.g. blades with reinforcing filaments}
- F01D 5/284: {Selection of ceramic materials}
- F01D 11/005: {Sealing means between non relatively rotating elements}
- F05D 2260/201: by impingement of a fluid
- F05D 2300/6033: Ceramic matrix composites [CMC]
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## 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.

## Claims

### Claim 1

A gas turbine engine system for compartmentalized airflow, the system comprising:
a static metal component;
a ceramic matrix composite (CMC) component forming a cavity with the static metal component and having first and second exit holes, the cavity being divided into 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 first and second exit holes of the CMC component that correspond to the respective passages; and
a rope seal that is positionable in a groove, and wherein the groove is at least one of:
formed between two raised landings with curved sidewalls extending from the static metal component and configured to seal against an inner surface of the CMC component by way of the rope seal; or
an arcuate groove formed in the static metal component and configured to seal against the inner surface of the CMC component by way of the rope seal.

### Claim 2 (depends on 1)

The system of claim 1, wherein the static metal component includes at least one of a vane spar and a combustor liner.

### Claim 3 (depends on 1)

The system of claim 1, further comprising at least one of first and second impingement holes in each section to receive airflow in the respective passages and at least one of the first and second exit holes in each section to remove airflow from the respective passages.

### Claim 4 (depends on 1)

The system of claim 1, wherein the rope seal divides the cavity into the respective passages between the static metal component and the CMC component.

### Claim 5 (depends on 1)

The system of claim 1, wherein the groove is the arcuate groove.

### Claim 6 (depends on 1)

The system of claim 1, wherein the groove is formed between the two raised landings with the curved sidewalls.

### Claim 7 (depends on 1)

The system of claim 1, wherein the respective passages are formed with a rope seal that includes at least one of aluminosilicate and aluminum oxide.

### Claim 8

A method of compartmentalizing airflow in a gas turbine engine system, the method comprising:
providing a static metal component;
providing a ceramic matrix composite (CMC) component forming a cavity with the static metal component and having first and second exit holes, the cavity being divided into a plurality of sections with respective passages to provide airflow between the spar and CMC component;
providing a groove including at least one of:
raised landings with curved sidewalls extending from the static metal component to accommodate a rope seal for sealing against an inner surface of the CMC component; or
an arcuate groove formed in the static metal component to accommodate the rope seal for sealing against the inner surface of the CMC component; and
controlling the airflow in the sections of the cavity along respective passages that receive the airflow into the cavity through the static metal component and remove the airflow from the cavity through the CMC component.

### Claim 9 (depends on 8)

The method of claim 8, wherein the static metal component includes at least one of a vane spar and a combustor liner.

### Claim 10 (depends on 8)

The method of claim 8, wherein an impingement hole is formed in each section to receive airflow in the respective passages and at least one of the first and second exit holes is formed in each section to remove and control airflow from the respective passages.

### Claim 11 (depends on 8)

The method of claim 8, further comprising:
providing the rope seal that divides the cavity into the respective passages between the static metal component and the CMC component.

### Claim 12 (depends on 8)

The method of claim 8, further comprising:
providing the groove including an arcuate groove.

### Claim 13 (depends on 8)

The method of claim 8, further comprising:
providing a groove between two raised landings with curved sidewalls extending from the static metal component to accommodate a rope seal for sealing against an inner surface of the CMC component.

### Claim 14 (depends on 8)

The method of claim 8, wherein the respective passages are formed with a rope seal that includes at least one of aluminosilicate and aluminum oxide.

### Claim 15

A method of compartmentalizing airflow in a gas turbine engine system, the method comprising:
providing a static metal component;
providing a ceramic matrix composite (CMC) component forming a cavity with the static metal component, the cavity being divided into sections with respective passages;
providing at least one impingement hole in each of the corresponding sections of the spar to receive airflow along the respective passages; and
providing at least one hole in each of the corresponding sections of the CMC component to remove the airflow from the cavity;
providing a groove including at least one of:
raised landings with curved sidewalls extending from the static metal component to accommodate a rope seal for sealing against an inner surface of the CMC component, or
an arcuate groove in the static metal component to accommodate the rope seal for sealing against the inner surface of the CMC component.

### Claim 16 (depends on 15)

The method of claim 15, wherein the static metal component includes at least one of a vane spar and a combustor liner.

### Claim 17 (depends on 15)

The method of claim 15, wherein providing the rope seal includes dividing the cavity into the respective passages between the static metal component and the CMC component.

### Claim 18 (depends on 15)

The method of claim 15, wherein providing the groove includes the arcuate groove.

### Claim 19 (depends on 15)

The method of claim 15, wherein providing the groove includes raised landings with curved sidewalls.

### Claim 20 (depends on 15)

The method of claim 15, wherein the respective passages are formed with the rope seal that includes at least one of aluminosilicate and aluminum oxide.