# US 9,752,585 B2 · Gas turbine engine architecture with intercooled twin centrifugal compressor

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- Number: US 9,752,585 B2
- Document ID: US9752585B2
- Status: Granted
- Kind: B2
- Application number: 14/209,326
- Filed: 2014-03-13
- Published: 2014-09-18
- Granted: 2017-09-05
- Earliest claimed: 2013-03-15
- Assignees: United Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Daniel B. Kupratis
- Web page: https://patentgrep.com/patent/US9752585B2

## CPC

- F04D 17/12: Multi-stage pumps
- F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)}
- F02C 3/08: the compressor comprising at least one radial stage (F02C3/10 takes precedence)
- F02C 3/107: with two or more rotors connected by power transmission
- F02C 7/143: before or between the compressor stages
- F02K 3/075: controlling flow ratio between flows
- F04D 29/441: {especially adapted for elastic fluid pumps}
- F04D 29/5833: {flow schemes and regulation thereto}
- F05D 2220/324: to drive unshrouded, low solidity propeller
- F05D 2250/311: the axes being in line
- F05D 2260/40311: of the epicyclical, planetary or differential type
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02)
- 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)
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- 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 gas turbine engine includes an intercooled twin centrifugal compressor. A pipe diffuser extends from the intercooled twin centrifugal compressor into an airflow path.

## Claims

### Claim 1

A gas turbine engine comprising:
an intercooled twin centrifugal compressor; and
a pipe diffuser that extends from said intercooled twin centrifugal compressor into an airflow path,
wherein said pipe diffuser extends around a Common Inlet Plenum in communication with said intercooled twin centrifugal compressor.

### Claim 2 (depends on 1)

The gas turbine engine as recited in claim 1, further comprising:
an outer case structure; and
an intermediate case structure,
wherein said airflow path is defined by the outer case structure and the intermediate case structure.

### Claim 3 (depends on 2)

The gas turbine engine as recited in claim 2, further comprising:
an inner case structure.

### Claim 4 (depends on 1)

The gas turbine engine as recited in claim 1, wherein said airflow path is a bypass airflow path.

### Claim 5 (depends on 1)

The gas turbine engine as recited in claim 1, wherein said intercooled twin centrifugal compressor includes a forward centrifugal impeller and an aft centrifugal impeller located respectively at the fore end and aft end of said Common Inlet Plenum.

### Claim 6 (depends on 5)

The gas turbine engine as recited in claim 5, wherein said forward centrifugal impeller communicates with said aft centrifugal impeller through said pipe diffuser.

### Claim 7 (depends on 6)

The gas turbine engine as recited in claim 6, wherein said pipe diffuser includes a forward manifold and an aft manifold.

### Claim 8 (depends on 7)

The gas turbine engine as recited in claim 7, wherein said forward manifold includes a multiple of manifold pipes, each of said multiple of manifold pipes includes a radial outward pipe, an axial pipe downstream of said radial outward pipe and a radial inward pipe downstream of said axial pipe.

### Claim 9 (depends on 8)

The gas turbine engine as recited in claim 8, wherein said radial inward pipe and said aft manifold combine downstream into a full annular duct.

### Claim 10 (depends on 9)

The gas turbine engine as recited in claim 9, wherein said full annular duct communicates with a second compressor axially aft of said intercooled twin centrifugal compressor.

### Claim 11 (depends on 8)

The gas turbine engine as recited in claim 8, further comprising a heat exchanger within said airflow path, said heat exchanger in communication with said axial pipe.

### Claim 12 (depends on 11)

The gas turbine engine as recited in claim 11, further comprising:
an outer case structure; and
an intermediate case structure,
wherein said airflow path is defined by the outer case structure and the intermediate case structure.

### Claim 13 (depends on 12)

The gas turbine engine as recited in claim 12, further comprising:
an inner case structure.

### Claim 14 (depends on 1)

The gas turbine engine as recited in claim 1, further comprising a heat exchanger within said airflow path, said heat exchanger in communication with said pipe diffuser.

### Claim 15 (depends on 14)

The gas turbine engine as recited in claim 14, further comprising:
an outer case structure;
an intermediate case structure; and
an inner case structure,
wherein said airflow path is defined by the outer case structure and the intermediate case structure.

### Claim 16

A method of operating a gas turbine engine comprising:
extending a pipe diffuser from an intercooled twin centrifugal compressor into an airflow path; and
mixing half of a core airflow from the intercooled twin centrifugal compressor with a cooled half of the core airflow from the intercooled twin centrifugal compressor.

### Claim 17 (depends on 16)

The method as recited in claim 16, wherein the gas turbine engine includes an outer case structure and an intermediate case structure, and wherein the airflow path is defined by the outer case structure and the intermediate case structure.

### Claim 18 (depends on 17)

The method as recited in claim 17, further comprising:
communicating the pipe diffuser with a heat exchanger within the airflow path.

### Claim 19 (depends on 16)

The method as recited in claim 16, wherein said mixing occurs upstream of a second compressor that is located axially aft of said intercooled twin centrifugal compressor.

### Claim 20

A gas turbine engine comprising:
an intercooled twin centrifugal compressor; and
a pipe diffuser that extends from said intercooled twin centrifugal compressor into an airflow path,
wherein said pipe diffuser foul's a screen around a Common Inlet Plenum in communication with said intercooled twin centrifugal compressor.