Gas turbine engine
Abstract
A gas turbine engine with a compressor rotor having compressor impulse blades that delivers gas at supersonic conditions to a stator. The stator includes a one or more aerodynamic ducts that each have a converging portion and a diverging portion for deceleration of the selected gas to subsonic conditions and to deliver a high pressure oxidant containing gas to flameholders. The flameholders may be provided as trapped vortex combustors, for combustion of a fuel to produce hot pressurized combustion gases. The hot pressurized combustion gases are choked before passing out of an aerodynamic duct to a turbine. Work is recovered in a turbine by expanding the combustion gases through impulse blades. By balancing the axial loading on compressor impulse blades and turbine impulse blades, asymmetrical thrust is minimized or avoided.
- Inventors:
- Issue Date:
- Research Org.:
- Dresser-Rand Company, Olean, NY (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1241316
- Patent Number(s):
- 9279334
- Application Number:
- 13/542,674
- 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; 42 ENGINEERING
Citation Formats
Lawlor, Shawn P., and Roberts, II, William Byron. Gas turbine engine. United States: N. p., 2016.
Web.
Lawlor, Shawn P., & Roberts, II, William Byron. Gas turbine engine. United States.
Lawlor, Shawn P., and Roberts, II, William Byron. Tue .
"Gas turbine engine". United States. https://www.osti.gov/servlets/purl/1241316.
@article{osti_1241316,
title = {Gas turbine engine},
author = {Lawlor, Shawn P. and Roberts, II, William Byron},
abstractNote = {A gas turbine engine with a compressor rotor having compressor impulse blades that delivers gas at supersonic conditions to a stator. The stator includes a one or more aerodynamic ducts that each have a converging portion and a diverging portion for deceleration of the selected gas to subsonic conditions and to deliver a high pressure oxidant containing gas to flameholders. The flameholders may be provided as trapped vortex combustors, for combustion of a fuel to produce hot pressurized combustion gases. The hot pressurized combustion gases are choked before passing out of an aerodynamic duct to a turbine. Work is recovered in a turbine by expanding the combustion gases through impulse blades. By balancing the axial loading on compressor impulse blades and turbine impulse blades, asymmetrical thrust is minimized or avoided.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Mar 08 00:00:00 EST 2016},
month = {Tue Mar 08 00:00:00 EST 2016}
}
Works referenced in this record:
Gas turbine power plant with supersonic shock compression ramps
patent, October 2008
- Lawlor, Shawn P.; Novaresi, Mark; Cornelius, Charles C.
- US Patent Document 7,434,400