Fluid injection systems for gas turbine engines
AssigneeRaytheon Technologies Corporation
InventorsDaniel B. Kupratis, Neil Terwilliger, Gary Roberge
Life of this patent
Estimating the term…
Abstract
A fluid injection system for a gas turbine engine may comprise a fluid injector configured to inject a fluid into an exhaust flow exiting a turbine section of the gas turbine engine. The fluid injector may be coupled to a turbine exit guide vane located at a forward end of an exhaust system of the gas turbine engine. The fluid may decrease a temperature of the exhaust flow exiting the turbine section and/or increase a thrust of the gas turbine engine.
Claims18
A fluid injection system of a gas turbine engine, comprising:
- a fluid injector configured to inject water into an exhaust flow exiting a turbine section of the gas turbine engine, wherein the fluid injector is coupled to an aft end of a turbine exit guide vane;
- a fluid supply tank fluidly coupled to the fluid injector;
- a conduit fluidly coupling the fluid supply tank to the fluid injector;
- and
- a heat exchanger thermally coupled to the conduit.
A gas turbine engine, comprising:
- a turbine;
- an exhaust system aft of the turbine, the exhaust system comprising a throat and a primary nozzle located radially outward of the throat;
- and
- a fluid injection system configured to inject a fluid into an exhaust gas exiting the turbine, the fluid being configured to evaporate without combusting and decrease a temperature of the exhaust gas exiting the turbine, wherein the fluid injection system comprises a fluid injector having a plurality of nozzles coupled to an aft end of a turbine exit guide vane of the turbine, the turbine exit guide vane and the fluid injector being located at a forward end of the exhaust system.
A gas turbine engine, comprising:
- a turbine section;
- an exhaust system aft of the turbine section, comprising a throat and a primary nozzle located radially outward of the throat, wherein a radially inward surface of the primary nozzle defines a portion of a first exhaust path for a core airflow, and wherein a radially outward surface of the primary nozzle defines a portion of a second exhaust path for a bypass airflow;
- and
- a means for injecting a fluid into the core airflow exiting the turbine section, wherein the fluid is configured to decrease a temperature of the core airflow exiting the turbine section upon the fluid being injected into the core airflow exiting the turbine section, such that the temperature of the core airflow exiting the turbine section is greater than a temperature of the core airflow at a forward end of the exhaust system.
A fluid injection system of a gas turbine engine, comprising:
- a fluid injector configured to inject water into an exhaust flow exiting a turbine section of the gas turbine engine, wherein the fluid injector is coupled to an aft end of a turbine exit guide vane;
- a valve configured to regulate a flow of the water from the fluid injector;
- an electromechanical actuator operably coupled to the valve;
- and
- a controller in operable communication with the electromechanical actuator, wherein the controller is configured to command the electromechanical actuator to actuate the valve to an open position during a take-off operating condition.
Dependencies are inferred from the claim text.