# US 10,767,562 B2 · Modulated cooled P3 air for impeller

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- Number: US 10,767,562 B2
- Document ID: US10767562B2
- Status: Granted
- Kind: B2
- Application number: 14/565,524
- Filed: 2014-12-10
- Published: 2016-06-16
- Granted: 2020-09-08
- Earliest claimed: 2014-12-10
- Assignees: Pratt & Whitney Canada Corp.
- Applicants: Pratt & Whitney Canada Corp.
- Inventors: Xiaoliu Liu
- Web page: https://patentgrep.com/patent/US10767562B2

## CPC

- F02C 7/185: {Cooling means for reducing the temperature of the cooling air or gas}
- F01D 5/082: {on the side of the rotor disc}
- F02C 7/143: before or between the compressor stages
- F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)}
- F04D 29/0516: {balancing pistons}
- F04D 29/284: {for compressors}
- F04D 29/522: {especially adapted for elastic fluid pumps}
- F04D 29/584: {cooling or heating the machine (F04D29/5846, F04D29/5853 take precedence)}
- F05D 2260/213: by the provision of a heat exchanger within the cooling circuit
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- 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)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F04D: NON-POSITIVE-DISPLACEMENT PUMPS (engine fuel-injection pumps F02M; ion pumps H01J41/12; electrodynamic pumps H02K44/02)
- 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 method and apparatus using a cooler to selectively cool P3 air directed into an impeller rear cavity of a gas turbine engine during engine high power levels, may include connection of the cooler to a low pressure compressor bleed-off valve apparatus that is modulated to be closed during engine high power levels to create a pressure differential over the bleed-off valve apparatus, to drive a stream of low pressure compressor air as a cooling work fluid under such pressure differential to selectively flow through the cooler.

## Claims

### Claim 1

A gas turbine engine comprising a compressor section, including:
a bleed-off valve connected in a bleed-air flow passage, for selectively bleeding low pressure air from the compressor section through the bleed-air flow passage to an outlet of an exhaust duct when the bleed-off valve is open, the outlet disposed downstream of a turbine section;
a cooler having a first passage connected to the bleed-air flow passage in parallel with the bleed-off valve to allow a stream of said low pressure air to flow through the cooler and to bypass the bleed-off valve when the bleed-off valve is closed, the cooler having a second passage for directing a stream of high pressure air bled from a plenum around a combustion chamber through the cooler before delivering the stream of said high pressure air to an impeller rear cavity formed behind an impeller hub of the compressor section, the stream of said high pressure air having a higher pressure than the stream of said low pressure air;
wherein the stream of said low pressure air through the first passage of the cooler is modulated by the bleed-off valve parallel to the first passage of the cooler, so as to selectively cool the stream of said high pressure air flowing through the second passage of the cooler with the stream of said low pressure air; and
a controller configured to control the bleed-off valve such that the bleed-off valve is closed during engine high power and is open during engine low power.

### Claim 2 (depends on 1)

The gas turbine engine as defined in claim 1 wherein the compressor section comprises a low pressure compressor, and a high pressure compressor including an impeller and defining the impeller rear cavity.

### Claim 3 (depends on 2)

The gas turbine engine as defined in claim 2 wherein the bleed-air flow passage is connected to a main fluid path of the gas turbine engine at a location downstream of the low pressure compressor and upstream of the high pressure compressor.

### Claim 4 (depends on 1)

The gas turbine engine as defined in claim 1 wherein the bleed-off valve forms part of the bleed-air flow passage and has a first air flow resistance lower than a second air flow resistance of the first passage of the cooler.

### Claim 5

A method of cooling an impeller of a compressor of a gas turbine engine, the method comprising:
bleeding low pressure air from the compressor of the gas turbine engine through a bleed-air flow passage, the bleed-air flow passage in fluid communication with a first passage of a cooler;
bleeding a stream of high pressure air from a plenum around a combustion chamber, the stream of said high pressure air having a greater pressure than the low pressure air;
continuously circulating the stream of said high pressure air through a second passage of the cooler to a cavity adjacent a hub of the impeller; and
modulating a cooling of the stream of said high pressure air in the cooler by modulating a flow of the low pressure air bypassing the first passage of the cooler while flowing through the bleed-air flow passage to exit the bleed-air flow passage downstream of a turbine section of the gas turbine engine, wherein modulating the flow of the low pressure air bypassing the first passage of the cooler while flowing through the bleed-air flow passage includes selectively opening and closing a bleed-off valve of the bleed-air flow passage, the bleed-off valve being connected to the bleed-air flow passage in parallel with the first passage of the cooler, including closing the bleed-off valve during engine high power levels and opening the bleed-off valve during engine low power levels.

### Claim 6 (depends on 5)

The method as defined in claim 5, wherein closing the bleed-off valve creates a pressure differential in the low pressure air across the bleed-off valve when the gas turbine engine is operated at the high power levels, and opening the bleed-off valve bleeds the low pressure air to reduce the pressure differential when the gas turbine engine is operated at the low power levels.

### Claim 7 (depends on 5)

The method as defined in claim 5, comprising reducing transition thermal gradients of the impeller of the gas turbine engine during engine operation between the engine high power levels and the engine low power levels by modulating the flow of the low pressure air bypassing the first passage to supply the low pressure air in the first passage only during said engine high power levels.

### Claim 8 (depends on 7)

The method as defined in claim 7 wherein modulating the flow of the low pressure air bypassing the first passage is achieved via modulating the bleed-off valve.

### Claim 9 (depends on 7)

The method as defined in claim 7 wherein modulating the flow of the low pressure air bypassing the first passage is achieved by connecting the cooler to the bleed-off valve modulated to be closed during said engine high power levels to create a pressure differential of the low pressure air over the bleed-off valve, and modulated to be open to allow the low pressure air to bypass the cooler during said engine low power levels, thereby reducing said pressure differential.

### Claim 10 (depends on 9)

The method as claimed in claim 9 wherein the cooler and the bleed-off valve are connected in a parallel relationship, one with the other, to thereby supply the low pressure air under said pressure differential to the cooler as a cooling work fluid to cool the stream of said high pressure air before entering into the cavity of the impeller only during the engine high power levels.