GAS TURBINE ENGINE WITH SUPERSONIC COMPRESSOR

Number of patents in Portfolio can not be more than 2000

United States of America Patent

SERIAL NO

14881288

Stats

ATTORNEY / AGENT: (SPONSORED)

Importance

Loading Importance Indicators... loading....

Abstract

See full text

A gas turbine engine having a compressor section using blades on a rotor to deliver a gas at supersonic conditions to a stator. The stator includes one or more of aerodynamic ducts that have converging and diverging portions for deceleration of the gas to subsonic conditions and to deliver a high pressure gas to combustors. The aerodynamic ducts include structures for changing the effective contraction ratio to enable starting even when designed for high pressure ratios, and structures for boundary layer control. In an embodiment, aerodynamic ducts are provided having an aspect ratio of two to one (2:1) or more, when viewed in cross-section orthogonal to flow direction at an entrance to the aerodynamic duct.

Loading the Abstract Image... loading....

First Claim

See full text

Family

Loading Family data... loading....

Patent Owner(s)

Patent OwnerAddress
DRESSER-RAND COMPANYOLEAN NY

International Classification(s)

Inventor(s)

Inventor Name Address # of filed Patents Total Citations
Lawlor, Shawn P Bellevue, US 36 653
Roberts,, II William Byron Wellington, US 5 14

Cited Art Landscape

Load Citation

Patent Citation Ranking

Forward Cite Landscape

Load Citation