Cooling system for engine and aircraft air
US-9239005-B2 · Jan 19, 2016 · US
Intercooled cooling air with dual pass heat exchanger
US9850819B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9850819-B2 |
| Application number | US-201514695504-A |
| Country | US |
| Kind code | B2 |
| Filing date | Apr 24, 2015 |
| Priority date | Apr 24, 2015 |
| Publication date | Dec 26, 2017 |
| Grant date | Dec 26, 2017 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
A gas turbine engine comprises a main compressor section having a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses ng air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. An intercooling system for a gas turbine engine is also disclosed.
First claim
Opening claim text (preview).
What is claimed is: 1. A gas turbine engine comprising; a main compressor section having a downstream most end, and more upstream locations; a turbine section having a high pressure turbine; a tap tapping air from at least one of said more upstream locations in said compressor section, and where said air is at a pressure that is lower than a pressure at said downstream most end, passing said tapped air through a heat exchanger and then to a cooling compressor, said cooling compressor compressing air downstream of said heat exchanger, and delivering air into said high pressure turbine; and said heat exchanger having at least two passes, with one of said passes passing air radially outwardly, and a second of said passes returning the air radially inwardly to the cooling compressor. 2. The gas turbine engine as set forth in claim 1 , wherein a main fan delivers bypass air into a bypass duct and into said main compressor section and said heat exchanger positioned within said bypass duct to be cooled by bypass air. 3. The gas turbine engine as set forth in claim 2 , wherein said cooling compressor includes a centrifugal compressor impeller. 4. The gas turbine engine as set forth in claim 3 , wherein said first pass is positioned upstream of said second pass in said bypass duct. 5. The gas turbine engine as set forth in claim 2 , wherein said first pass is positioned upstream of said second pass in said bypass duct. 6. The gas turbine engine as set forth in claim 2 , wherein said at least one of said more upstream locations is in a high pressure compressor. 7. The gas turbine engine as set forth in claim 2 , wherein said at least one of said more upstream locations is in a low pressure compressor. 8. The gas turbine engine as set forth in claim 1 , wherein an auxiliary fan is positioned upstream of the heat exchanger. 9. The gas turbine engine as set forth in claim 1 , wherein said at least one of said more upstream locations is in a high pressure compressor. 10. The gas turbine engine as set forth in claim 1 , wherein said at least one of said more upstream locations is in a low pressure compressor.
Assignees
Inventors
Classifications
Bypassing the fluid · CPC title
the first stage of a turbine · CPC title
bidirectional, i.e. in opposite, alternating directions · CPC title
- F02C7/185Primary
Cooling means for reducing the temperature of the cooling air or gas · CPC title
by the provision of a heat exchanger within the cooling circuit · CPC title
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Frequently asked questions
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- What does patent US9850819B2 cover?
- A gas turbine engine comprises a main compressor section having a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses ng air downstream of the hea…
- Who is the assignee on this patent?
- United Technologies Corp
- What technology area does this patent fall under?
- Primary CPC classification F02C7/185. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Dec 26 2017 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 3 related publications on this page (citations in our corpus or others sharing the same primary CPC).