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.:
Date of Patent:
Feb. 23, 2016
Filed:
Nov. 18, 2013
Applicant:
Honeywell International Inc., Morristown, NJ (US);
Inventors:
Assignee:
HONEYWELL INTERNATIONAL INC., Morris Plains, NJ (US);
Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
B64D 31/06 (2006.01); F02C 9/16 (2006.01); F01D 11/20 (2006.01); F01D 11/24 (2006.01); F02C 7/18 (2006.01);
U.S. Cl.
CPC ...
B64D 31/06 (2013.01); F01D 11/20 (2013.01); F01D 11/24 (2013.01); F02C 7/18 (2013.01); F02C 9/16 (2013.01); F05D 2260/20 (2013.01); F05D 2260/201 (2013.01); F05D 2260/57 (2013.01); F05D 2270/07 (2013.01); F05D 2270/44 (2013.01);
Abstract
A system and method of controlling turbine blade tip-to-static structure clearance in a gas turbine engine includes processing aircraft data to determine when the aircraft is flying at altitude cruise conditions. When the aircraft is not flying at altitude cruise conditions, then compressor discharge air is directed to impinge upon at least a portion of the turbine shroud. Upon determining that the aircraft is flying at altitude cruise conditions, the compressor discharge air is directed to flow across at least a portion of the turbine case and to impinge upon at least a portion of the turbine shroud.