Stationary gas turbine power system and related method
OwnerRobert G. Suretteinventor
Life of this patent
Estimating the term…
Abstract
This disclosure provides a stationary gas turbine power system that develops a reduced back pressure for the gas turbine engine and thus greater efficiency. An enclosed ejector is positioned downstream of the engine's exhaust plane, and means such as a downstream diffuser cause the exhaust stream to entrain air from the ejector enclosure, by natural pumping action, so as to develop a sub-atmospheric pressure within that enclosure and thus at the engine's exhaust plane. This provides substantially improved engine efficiency. The diffuser recovers the static pressure to a level sufficient to drive any downstream devices.
Claims21
A stationary gas turbine power system, comprising:
- a stationary gas turbine engine having an exhaust plane through which an exhaust stream is expelled;
- an ejector that includes an enclosure defining a space that is ported to a region located downstream of the exhaust plane of the gas turbine engine;
- and
- means for developing a sub-atmospheric pressure at the ejector and at the exhaust plane, to reduce the back pressure applied to the gas turbine engine and thereby improve the engine's efficiency.
A stationary gas turbine power system comprising:
- a stationary gas turbine engine having an exhaust plane through which an exhaust stream is expelled, the gas turbine engine including a generally annular exhaust port and a generally conical nozzle plug projecting downstream from the engine's exhaust plane;
- an ejector located downstream of the exhaust plane of the gas turbine engine:
- and
- means for developing a sub-atmospheric pressure at the ejector and at the exhaust plane, to reduce the back pressure applied to the gas turbine engine and thereby improve the engine's efficiency;
- wherein the ejector and the means for developing a sub-atmospheric pressure, together, include a generally conical wall encircling and concentric with the nozzle plug, for defining an annular exhaust flow path downstream of the engine's exhaust plane.
A stationary gas turbine power system comprising:
- a gas turbine engine having an exhaust plane through which an exhaust stream is expelled;
- an ejector that includes an enclosure defining space that is ported to a region located downstream of the exhaust plane of the gas turbine engine;
- and
- a diffuser, located downstream of the ejector, that slows the speed of the exhaust stream and thereby recovers the exhaust stream's pressure to a predetermined level;
- wherein the ejector reduces the pressure present at the exhaust plane of the gas turbine engine.
A stationary gas turbine power system comprising:
- a gas turbine engine having an exhaust plane through which an exhaust stream is expelled, the gas turbine engine including a generally annular exhaust port and a generally conical nozzle plug projecting downstream from the engine's exhaust plane;
- an ejector located downstream of the exhaust plane of the gas turbine engine:
- and
- a diffuser, located downstream of the ejector, that slows the speed of the exhaust stream and thereby recovers the exhaust stream's pressure to a predetermined level;
- wherein the ejector reduces the pressure present at the exhaust plane of the gas turbine engine;
- and wherein the ejector and the diffuser, together, include a generally conical wall encircling and concentric with the nozzle plug, for defining an annular exhaust flow path downstream of the engine's exhaust plane.
A method for operating a stationary gas turbine power system having a gas turbine engine with an exhaust plane through which an exhaust stream is expelled, comprising:
- positioning an ejector downstream of the exhaust plane of the gas turbine engine, the ejector including an annular port that encircles the exhaust stream;
- and
- positioning an enclosure around the annular port of the ejector, so as to define a chamber that is closed to the surrounding atmosphere, and developing a sub-atmospheric pressure at the ejector and at the exhaust plane, to reduce the back pressure applied to the gas turbine engine and thereby improve the engine's efficiency.
Dependencies are inferred from the claim text.