# US 9,752,440 B2 · Turbine component having surface cooling channels and method of forming same

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- Number: US 9,752,440 B2
- Document ID: US9752440B2
- Status: Granted
- Kind: B2
- Application number: 14/725,695
- Filed: 2015-05-29
- Published: 2016-12-01
- Granted: 2017-09-05
- Earliest claimed: 2015-05-29
- Assignees: General Electric Company
- Applicants: General Electric Company
- Inventors: Carlos Miguel Miranda; Andrew Lee Trimmer; Srikanth Chandrudu Kottilingam; Benjamin Paul Lacy
- Web page: https://patentgrep.com/patent/US9752440B2

## CPC

- F01D 5/18: Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades
- F01D 5/186: {Film cooling (F01D5/187 takes precedence)}
- F01D 5/187: {Convection cooling}
- F01D 5/288: {Protective coatings for blades}
- F01D 9/041: {using blades (F01D5/148 takes precedence)}
- F01D 25/12: Cooling
- F02C 3/04: having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16)
- F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)}
- F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)}
- F05D 2220/32: in gas turbines
- F05D 2230/10: by removing material
- F05D 2240/128: Nozzles
- F05D 2240/30: Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D 2240/35: Combustors or associated equipment
- F05D 2260/204: by the use of microcircuits
- F05D 2270/3062: of the auxiliary fluid for heating or cooling purposes
- 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)
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16)
- 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 component for a turbine engine includes a substrate that includes a first surface, and an insert coupled to the substrate proximate the substrate first surface. The component also includes a channel. The channel is defined by a first channel wall formed in the substrate and a second channel wall formed by at least one coating disposed on the substrate first surface. The component further includes an inlet opening defined in flow communication with the channel. The inlet opening is defined by a first inlet wall formed in the substrate and a second inlet wall defined by the insert.

## Claims

### Claim 1

A component for a turbine engine, said component comprising:
a substrate comprising a substrate first surface, said substrate first surface comprising a recess defined therein;
an insert coupled to said substrate proximate said substrate first surface, wherein said insert is shaped complementary to a shape of said recess;
a channel defined by a first channel wall formed in said substrate and a second channel wall formed by at least one coating disposed on said substrate first surface;
an inlet opening defined in flow communication with said channel, said inlet opening defined by a first inlet wall formed in said substrate and a second inlet wall defined by said insert; and
a transition region between said channel and said inlet opening such that said transition region is in flow communication with said channel and is at least partially defined by a first transition wall formed in said substrate and a second transition wall formed by said insert.

### Claim 2 (depends on 1)

The component of claim 1, wherein a longitudinal axis of said inlet opening intersects a longitudinal axis of said channel at an angle that is obtuse.

### Claim 3 (depends on 1)

The component of claim 1, wherein said insert comprises a plug disposed in said inlet opening proximate said substrate first surface.

### Claim 4 (depends on 1)

The component of claim 1, wherein a depth of said transition region decreases between said inlet opening and said channel.

### Claim 5

A turbine engine comprising:
a combustor section configured to generate a hot gas; and
a component disposed along a path configured to be traversed by the hot gas, said component comprising:
a substrate comprising a substrate first surface, said substrate first surface comprising a recess defined therein;
an insert coupled to said substrate proximate said substrate first surface, wherein said insert is shaped complementary to a shape of said recess;
a channel defined by a first channel wall formed in said substrate and a second channel wall formed by at least one coating disposed on said substrate first surface;
an inlet opening defined in flow communication with said channel, said inlet opening defined by a first inlet wall formed in said substrate and a second inlet wall defined by said insert; and
a transition region disposed between said channel and said inlet opening such that said transition region is in flow communication with said channel and is at least partially defined by a first transition wall formed in said substrate and a second transition wall formed by said insert.

### Claim 6 (depends on 5)

The turbine engine of claim 5, wherein a longitudinal axis of said inlet opening intersects a longitudinal axis of said channel at an angle that is obtuse.

### Claim 7 (depends on 5)

The turbine engine of claim 5, wherein said insert comprises a plug disposed in said inlet opening proximate said substrate first surface.

### Claim 8 (depends on 5)

The turbine engine of claim 5, wherein a depth of said transition region decreases between said inlet opening and said channel.

### Claim 9

A method of forming a component for a turbine engine, said method comprising:
forming a first channel wall of a channel in a substrate;
forming a first inlet wall of an inlet opening in the substrate;
forming a recess in the substrate first surface;
coupling an insert to the substrate proximate a first surface of the substrate, wherein the insert defines a second inlet wall of the inlet opening, and wherein the insert is shaped complementary to a shape of the recess;
disposing at least one coating on the substrate first surface, wherein the at least one coating forms a second channel wall of the channel, the inlet opening defined in flow communication with the channel; and
forming a transition region between the channel and the inlet opening such that the transition region is in flow communication with the channel and is at least partially defined by a first transition wall formed in the substrate and a second transition wall formed by the insert.

### Claim 10 (depends on 9)

The method of claim 9, further comprising forming the first inlet wall such that a longitudinal axis of the inlet opening intersects a longitudinal axis of the channel at an angle that is obtuse.

### Claim 11 (depends on 9)

The method of claim 9, wherein said coupling the insert to the substrate comprises disposing a plug in the inlet opening proximate the substrate first surface.

### Claim 12 (depends on 9)

The method of claim 9, further comprising forming the transition region such that a depth of the transition region decreases between the inlet opening and the channel.