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:
Mar. 31, 2020

Filed:

Aug. 20, 2013
Applicant:

United Technologies Corporation, Hartford, CT (US);

Inventors:

Bruce L. Morin, Springfield, MA (US);

David A. Topol, West Hartford, CT (US);

Detlef Korte, Munich, DE;

Assignees:

UNITED TECHNOLOGIES CORPORATION, Farmington, CT (US);

MTU AERO ENGINES AG, Munich, DE;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02C 7/24 (2006.01); F02K 3/06 (2006.01);
U.S. Cl.
CPC ...
F02C 7/24 (2013.01); F02K 3/06 (2013.01); F05D 2200/36 (2013.01); F05D 2210/31 (2013.01); F05D 2240/301 (2013.01); F05D 2240/307 (2013.01); Y02T 50/673 (2013.01);
Abstract

A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a turbine section including a fan drive turbine, a compressor section driven by the turbine section, a geared architecture driven by the fan drive turbine, and a fan driven by the fan drive turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to about 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to about 0.5 at an approach speed.


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