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. 07, 2023

Filed:

Nov. 23, 2021
Applicant:

Raytheon Technologies Corporation, Farmington, CT (US);

Inventor:

Jayant Sabnis, Glastonbury, CT (US);

Assignee:

Raytheon Technologies Corporation, Farmington, CT (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02K 3/075 (2006.01); F02K 3/06 (2006.01); F02C 3/107 (2006.01); F01D 15/12 (2006.01); F02K 1/52 (2006.01); B64D 27/10 (2006.01); F02C 3/04 (2006.01); F01D 5/06 (2006.01); F04D 19/02 (2006.01); F04D 29/32 (2006.01); F01D 19/02 (2006.01);
U.S. Cl.
CPC ...
F02K 3/075 (2013.01); B64D 27/10 (2013.01); F01D 5/06 (2013.01); F01D 15/12 (2013.01); F01D 19/02 (2013.01); F02C 3/04 (2013.01); F02C 3/107 (2013.01); F02K 1/52 (2013.01); F02K 3/06 (2013.01); F04D 19/02 (2013.01); F04D 29/325 (2013.01); F05D 2220/323 (2013.01); F05D 2220/36 (2013.01); F05D 2240/35 (2013.01);
Abstract

A disclosed gas turbine engine includes a gas generator section for generating a gas stream flow and a propulsor section for generating propulsive thrust as a mass flow rate of air through a bypass flow path. The propulsor section includes a fan driven by a power turbine through a speed reduction device at a second rotational speed lower than a first rotational speed of the power turbine. An Engine Unit Thrust Parameter ('EUTP') defined as net engine thrust divided by a product of the mass flow rate of air through the bypass flow path, a tip diameter of the fan and the first rotational speed of the power turbine is between 0.05 and 0.13 during operation of the gas turbine engine.


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