Engine bleed air ducting into heat exchanger

Patent metadata

Field	Value
Publication number	US-11078837-B2
Application number	US-201916269151-A
Country	US
Kind code	B2
Filing date	Feb 6, 2019
Priority date	Feb 6, 2019
Publication date	Aug 3, 2021
Grant date	Aug 3, 2021

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.

First claim

The invention claimed is:

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.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Zysman Steven H
• Blume Karl D
• Anderson James H
• Teufel Holly
• Clauson Jesse W
• Campbell Xiaojun
• Taylor William O
• Kaiser Graham A
• Milenkovic Karl
• Rhodes Michael C
• Dolma Tsering

Classifications

• F05D2260/606

  Bypassing the fluid · CPC title

• F05D2260/40311

  of the epicyclical, planetary or differential type · CPC title

• F05D2260/232

  characterized by the cooling medium · CPC title

• F02C7/36

  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) · CPC title

• F02C7/18

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title