# US 11,298,742 B2 · Hybrid component with cooling channels and corresponding process

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- Number: US 11,298,742 B2
- Document ID: US11298742B2
- Status: Granted
- Kind: B2
- Application number: 16/716,166
- Filed: 2019-12-16
- Published: 2020-04-16
- Granted: 2022-04-12
- Earliest claimed: 2019-12-16
- Assignees: Siemens Aktiengesellschaft
- Applicants: Siemens Aktiengesellschaft
- Inventors: Gary B. Merrill; Nicholas F. Martin, Jr.
- Web page: https://patentgrep.com/patent/US11298742B2

## CPC

- B22C 9/04: Use of lost patterns
- B22C 7/02: Lost patterns
- B22C 9/10: Cores; Manufacture or installation of cores {(breaker cores B22C9/084)}
- B22D 29/002: {by leaching, washing or dissolving}
- 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 5/187: {Convection cooling}
- F01D 5/282: {Selecting composite materials, e.g. blades with reinforcing filaments}
- F01D 5/284: {Selection of ceramic materials}
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F01D 25/12: Cooling
- F05D 2220/32: in gas turbines
- F05D 2230/21: by casting
- F05D 2260/20: Heat transfer, e.g. cooling
- F05D 2260/221: Improvement of heat transfer
- F05D 2300/175: Superalloys
- F05D 2300/20: Oxide or non-oxide ceramics
- F05D 2300/5023: Thermal capacity
- F05D 2300/6012: Woven fabrics
- F05D 2300/6033: Ceramic matrix composites [CMC]
- B22C: FOUNDRY MOULDING (moulding refractory materials in general B28B)
- B22D: CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES (shaping of plastics or substances in a plastic state B29C; metallurgical processing, selection of substances to be added to metal C21, C22)
- 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

## Abstract

A component is provided and includes a core including a ceramic matrix composite material, one or more cooling channels formed about the core, an outer metal shell disposed about the core and the one or more cooling channels and a protective material between the core and the outer metal shell. The one or more cooling channels are formed about the core as an array of cooling channels in the protective material.

## Claims

### Claim 1

A component comprising:
a core comprising a ceramic matrix composite material;
one or more cooling channels formed about the core;
an outer metal shell disposed about the core and the one or more cooling channels; and
a protective material between the core and the outer metal shell,
wherein:
the one or more cooling channels are formed about the core as an array of cooling channels in the protective material,
the core has an entirely continuous external surface with an entirety of each of the one or more cooling channels being outside of the external surface of the core, and
each of the one or more cooling channels protrudes beyond the protective material and into the outer metal shell.

### Claim 2 (depends on 1)

The component of claim 1, wherein the component comprises a component of a gas turbine engine.

### Claim 3 (depends on 1)

The component of claim 1, wherein each of the one or more cooling channels is entirely encompassed within the protective material.

### Claim 4 (depends on 1)

The component of claim 1, wherein the protective material is formed as a ring and the array of the cooling channels is ring-shaped.

### Claim 5

A component comprising:
a core comprising a ceramic matrix composite material;
one or more cooling channels formed about the core;
an outer metal shell disposed about the core and the one or more cooling channels; and
a protective material between the core and the outer metal shell,
wherein:
the one or more cooling channels are formed about the core and the protective material as an array of cooling channels in the outer metal shell, and
the protective material has an entirely continuous external surface with an entirety of each of the one or more cooling channels being outside of the external surface of the protective material.

### Claim 6 (depends on 5)

The component of claim 5, wherein the component comprises a component of a gas turbine engine.