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.

Date of Patent:
Jan. 09, 2024

Filed:

Apr. 18, 2022
Applicant:

Raytheon Technologies Corporation, Farmington, CT (US);

Inventors:

Edward J. Gallagher, West Hartford, CT (US);

Lisa I. Brilliant, Middletown, CT (US);

Joseph C. Straccia, Middletown, CT (US);

Stanley J. Balamucki, The Villages, FL (US);

Mark A. Stephens, Wethersfield, CT (US);

Kate Hudon, Superior, CO (US);

Assignee:

RTX Corporation, Farmington, CT (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F04D 29/32 (2006.01); F04D 29/54 (2006.01); F01D 5/14 (2006.01); F01D 9/02 (2006.01); F02C 3/04 (2006.01); F02C 7/36 (2006.01); F02K 3/06 (2006.01); F04D 29/38 (2006.01);
U.S. Cl.
CPC ...
F04D 29/324 (2013.01); F01D 5/14 (2013.01); F01D 5/141 (2013.01); F01D 9/02 (2013.01); F02C 3/04 (2013.01); F02C 7/36 (2013.01); F02K 3/06 (2013.01); F04D 29/384 (2013.01); F04D 29/544 (2013.01); F05D 2220/32 (2013.01); F05D 2240/35 (2013.01); F05D 2250/71 (2013.01); F05D 2260/4031 (2013.01); Y02T 50/60 (2013.01);
Abstract

A gas turbine engine includes a combustor section arranged between a compressor section and a turbine section. The compressor section includes at least a low pressure compressor and a high pressure compressor. The high pressure compressor is arranged upstream of the combustor section. A fan section is included. The low pressure compressor is downstream from the fan section. An airfoil is arranged in the low pressure compressor and includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has an axial stacking offset at a 10% span position that is positive and greater than or equal to an axial stacking offset at the 100% span position. The axial stacking offsets measured relative to an aftward direction.


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