Gas turbine engine
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.
- Research Organization:
- Dresser-Rand Company, Olean, NY (United States)
- Sponsoring Organization:
- USDOE
- DOE Contract Number:
- FE0000493
- Assignee:
- Dresser-Rand Company (Olean, NY)
- Patent Number(s):
- 9,279,334
- Application Number:
- 13/542,674
- OSTI ID:
- 1241316
- Resource Relation:
- Patent File Date: 2012 Jul 06
- Country of Publication:
- United States
- Language:
- English
Gas turbine power plant with supersonic shock compression ramps
|
patent | October 2008 |
Similar Records
Supersonic compressor
Gas turbine annular combustor with radial dilution air injection