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:
Oct. 03, 2023

Filed:

Feb. 01, 2022
Applicant:

Raytheon Technologies Corporation, Farmington, CT (US);

Inventors:

Simon W. Evans, Farmington, CT (US);

Yuan Dong, Glastonbury, CT (US);

Sean Nolan, Wethersfield, CT (US);

Assignee:

RTX CORPORATION, Farmington, CT (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F04D 29/38 (2006.01); F01D 5/14 (2006.01); F04D 19/02 (2006.01); F04D 29/32 (2006.01);
U.S. Cl.
CPC ...
F04D 29/384 (2013.01); F01D 5/145 (2013.01); F04D 19/02 (2013.01); F04D 29/324 (2013.01); F05D 2210/30 (2013.01); F05D 2220/3216 (2013.01); F05D 2240/307 (2013.01); F05D 2260/821 (2013.01); F05D 2270/3013 (2013.01); Y02T 50/60 (2013.01);
Abstract

A compressor section for a gas turbine engine includes a blade including a platform, a tip and an airfoil extending between the platform and tip. The airfoil includes a root portion adjacent to the platform, a midspan portion and a tip portion. Each of the root portion, midspan portion and tip portion define a meridional velocity at stage exit with the tip portion including a first meridional velocity greater than a second meridional velocity of the midspan portion. A blade for an axial compressor of a gas turbine engine and a method of operating a compressor section of a gas turbine engine are also disclosed.


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