# US 11,078,837 B2 · Engine bleed air ducting into heat exchanger

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- Number: US 11,078,837 B2
- Document ID: US11078837B2
- Status: Granted
- Kind: B2
- Application number: 16/269,151
- Filed: 2019-02-06
- Published: 2020-08-06
- Granted: 2021-08-03
- Earliest claimed: 2019-02-06
- Assignees: Raytheon Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Steven H. Zysman; Karl D. Blume; James H. Anderson; Holly Teufel; Jesse W. Clauson; Xiaojun Campbell; William O. Taylor; Graham A. Kaiser; Karl Milenkovic; Michael C. Rhodes; Tsering Dolma
- Web page: https://patentgrep.com/patent/US11078837B2

## CPC

- F02C 6/08: the gas being bled from the gas-turbine compressor
- F02C 7/06: Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M)
- F02C 7/14: of fluids in the plant {, e.g. lubricant or fuel (F02C7/185 takes precedence)}
- F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)}
- F02C 7/36: Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user ({F02C3/107 - F02C3/13 and} F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H)
- F02C 9/18: by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)}
- F02K 3/115: by means of indirect heat exchange
- F05D 2260/213: by the provision of a heat exchanger within the cooling circuit
- F05D 2260/232: characterized by the cooling medium
- F05D 2260/40311: of the epicyclical, planetary or differential type
- F05D 2260/606: Bypassing the fluid
- F05D 2260/98: Lubrication
- F05D 2270/303: Temperature
- 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)
- 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 a compressor section, a combustor, and a turbine section. A bleed tap taps air from the compressor section through a bleed valve. The bleed valve is selectively opened by a control to dump air from the compressor section to a dump outlet. A heat exchanger duct includes a duct air inlet to cool a fluid in a heat exchanger and a duct air outlet. The dump outlet is within the heat exchanger duct.

## Claims

### Claim 1

A gas turbine engine comprising:
a compressor section, a combustor, and a turbine section;
a bleed tap for tapping air from said compressor section through a bleed valve, the bleed valve selectively opened by a control to dump air from the compressor section to a dump outlet, said control for said bleed valve being operable to open said bleed valve under certain conditions to maintain stability of said compressor section, with said certain conditions including at least an idle condition, and when said gas turbine engine is accelerating at lower power or decelerating at high power;
a heat exchanger duct including a duct air inlet to cool a fluid in a heat exchanger and a duct air outlet, and said dump outlet being within said heat exchanger duct;
wherein a fan is positioned to selectively deliver air to said compressor, and also to deliver air into a bypass duct, and said duct air inlet takes air from said bypass duct, and said duct air outlet delivers air mixed from said duct air inlet and from said dump outlet back into said bypass duct;
wherein said dump outlet is downstream of a downstream end of said heat exchanger;
wherein said dump outlet is at a radially outer position within said heat exchanger duct;
wherein said heat exchanger duct has a downstream end provided with structure to withstand relatively high temperatures;
wherein said dump outlet directs air in a direction having a component which is radially outward relative to a rotational axis of the gas turbine engine, and there being an inner wall of said bypass duct, such that said dump outlet directs air in said direction to be radially outward, and away from said inner wall of said bypass duct; and
said dump outlet including a manifold and at least one orifice, with said manifold being mounted within said heat exchanger duct; and
wherein said downstream end of said heat exchanger duct is designed to have a temperature limit of greater than 1000° F. at an area immediately downstream of said duct air outlet of said heat exchanger duct.