The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Patent No.:

US 9797310 B1

PDF
Full Text
Expired
Date of Patent:
Oct. 24, 2017

Filed:

Apr. 02, 2015
Applicant:

General Electric Company, Schenectady, NY (US);

Inventors:

Sanji Ekanayake, Mableton, GA (US);

Joseph Paul Rizzo, Simpsonville, SC (US);

Alston Ilford Scipio, Mableton, GA (US);

Timothy Tahteh Yang, Greenville, SC (US);

Thomas Edward Wickert, Greenville, SC (US);

Assignee:

General Electric Company, Schenectady, NY (US);

Attorneys:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F02C 7/141 (2006.01); F01D 5/08 (2006.01); F01D 5/18 (2006.01); F01D 9/06 (2006.01); F01D 25/12 (2006.01); F01K 23/02 (2006.01); F02C 7/14 (2006.01); F02C 7/143 (2006.01); F02C 7/224 (2006.01); F02C 6/18 (2006.01); F02C 6/08 (2006.01);
U.S. Cl.
CPC ...
F02C 7/141 (2013.01); F01D 5/082 (2013.01); F01D 5/088 (2013.01); F01D 5/18 (2013.01); F01D 5/181 (2013.01); F01D 9/065 (2013.01); F01D 25/125 (2013.01); F01K 23/02 (2013.01); F02C 6/08 (2013.01); F02C 6/18 (2013.01); F02C 7/14 (2013.01); F02C 7/143 (2013.01); F02C 7/224 (2013.01); F05D 2260/208 (2013.01); Y02E 20/16 (2013.01);
Abstract

A turbomachine includes a compressor having an inter-stage gap between adjacent rows of rotor blades and stator vanes. A combustor is connected to the compressor, and a turbine is connected to the combustor. An intercooler is operatively connected to the compressor, and includes a first plurality of heat pipes that extend into the inter-stage gap. The first plurality of heat pipes are operatively connected to a first manifold, and the heat pipes and the first manifold are configured to transfer heat from the compressed airflow from the compressor to heat exchangers. A cooling system is operatively connected to the turbine, and includes a second plurality of heat pipes located in the turbine nozzles. The second plurality of heat pipes are operatively connected to a second manifold, and the heat pipes and the second manifold are configured to transfer heat from the turbine nozzles to the heat exchangers.


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