Gas turbine engine with supersonic compressor
Abstract
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.
- Inventors:
- Issue Date:
- Research Org.:
- Dresser-Rand Company, Olean, NY (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1223700
- Patent Number(s):
- 9163521
- Application Number:
- 13/542,669
- Assignee:
- Dresser-Rand Company (Olean, NY)
- Patent Classifications (CPCs):
-
F - MECHANICAL ENGINEERING F01 - MACHINES OR ENGINES IN GENERAL F01D - NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
F - MECHANICAL ENGINEERING F02 - COMBUSTION ENGINES F02C - GAS-TURBINE PLANTS
- DOE Contract Number:
- FE0000493
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2012 Jul 06
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 33 ADVANCED PROPULSION SYSTEMS
Citation Formats
Roberts, II, William Byron, and Lawlor, Shawn P. Gas turbine engine with supersonic compressor. United States: N. p., 2015.
Web.
Roberts, II, William Byron, & Lawlor, Shawn P. Gas turbine engine with supersonic compressor. United States.
Roberts, II, William Byron, and Lawlor, Shawn P. Tue .
"Gas turbine engine with supersonic compressor". United States. https://www.osti.gov/servlets/purl/1223700.
@article{osti_1223700,
title = {Gas turbine engine with supersonic compressor},
author = {Roberts, II, William Byron and Lawlor, Shawn P.},
abstractNote = {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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2015},
month = {10}
}
Works referenced in this record:
Flow energy conversion machine
patent, November 1987
- Garcia Cascajosa, Felix
- US Patent Document 4,707,978
Microjet creation and control of shock waves
patent, January 2013
- Alvi, Farrukh S.
- US Patent Document 8,359,825