System and method for tailoring rotor tip bleed air
AssigneeGeneral Electric Company
InventorsRollin G. Giffin, III, Harvey M. Maclin
Life of this patent
Estimating the term…
Abstract
A rotor tip bleed air tailoring system in which a rotor blade is located upstream from an outer stator vane and an inner stator vane. The inner stator vane and outer stator vane are separated by a splitter which extends to the tip region of the rotor blade and separates air exiting the rotor blade into regions of distinctly different pressures.
Claims12
A bleed air tailoring system for extracting pressurized air from a gas turbine engine airflow path in a compressor stage of the engine, the compressor stage including at least one annular array of rotor blades for increasing air pressure in the airflow path and at least one annular array of inner stator vanes for directing air exciting the rotor blades, the airflow path being defined by inner and outer annular casings within which the blades and vanes are positioned, the improvement comprising:
- separating means for separating the airflow path into a radially outward region of air and a radially inward region of air;
- and
- means for selectively extracting bleed air from said outward region of air;
- wherein said separating means comprises an annular splitter extending axially forward into a cutaway portion formed in a radially outer, trailing edge of each of said blades of said at least one annular array of rotor blades for extracting air at a pressure less than the air pressure at the trailing edge of said blades.
A bleed air tailoring system for extracting pressurized air from a gas turbine engine airflow path in a compressor stage of the engine, the compressor stage including at least one annular array of rotor blades for increasing air pressure in the airflow and at least one annular array of inner stator vanes for directing air exiting the rotor blades, the airflow path being defined by inner and outer annular casings within which the blades and vanes are positioned, the improvement comprising:
- separating means for separating the airflow path into a radially outward region of air and a radially inward region of air;
- and
- means for selectively extracting bleed air from said outward region of air;
- wherein said separating means comprises an annular splitter extending axially forward from an inner surface of the outer annular casing from a circumferential line located axially aft of the at least one annular array of rotor blades, said splitter including;
- an axially forward segment attached to the rotating blades for rotation therewith;
- an axially aft segment extending into a mating position adjacent said forward segment;
- and
- seal means between said forward and aft segments at said mating position for inhibiting air leakage therebetween.
A bleed air tailoring system for extracting pressurized air from a gas turbine engine airflow path in a compressor stage of the engine, the compressor stage including at least one annular array of rotor blades for increasing air pressure in the airflow path and at least one annular array of inner stator vanes for directing air exiting the rotor blades, the airflow path being defined by inner and outer annular casings within which the blades and vanes are positioned, the improvement comprising:
- separating means for separating the airflow path into a radially outward region of air and a radially inward region of air;
- means for selectively extracting bleed air from said outward region of air;
- and
- at least one outer stator vane located downstream of said rotor blade in the radially outward region of air;
- wherein said separating means comprises an annular splitter extending axially forward from an inner surface of the outer annular casing from a circumferential line located axially aft of the at least one annular array of rotor blades, said splitter being attached to the annular array of inner stator vanes;
- wherein said splitter comprises:
- an axially forward segment attached to the rotating blades for rotation therewith;
- an axially aft segment extending into a mating position adjacent said forward segment;
- and
- seal means between said forward and aft segments at said mating position for inhibiting air leakage therebetween.
A bleed air tailoring system for extracting pressurized air from a gas turbine engine airflow path in a compressor stage of the engine, the compressor stage including at least one annular array of rotor blades for increasing air pressure in the airflow path and at least one annular array of inner stator vanes for directing air exiting the rotor blades, the airflow path being defined by inner and outer annular casings within which the blades and vanes are positioned, the improvement comprising:
- separating means for separating the airflow path into a radially outward region of air and a radially inward region of air and means for selectively extracting bleed air from said outward region of air;
- at least one outer stator vane located downstream of said rotor blade in the radially outward region of air;
- wherein said separating means comprises an annular splitter extending axially forward from an inner surface of the outer annular casing from a circumferential line located axially aft of the at least one annular array of rotor blades, said splitter being attached to the annular array of inner stator vanes;
- wherein said blades in said annular array of rotating blades are each formed with a cutaway portion in a radially outer, trailing edge, said splitter extending into said cutaway portion for extracting air at a pressure less than the air pressure at the trailing edge of said blades.
A method for obtaining bleed air at a preselected pressure from a compressor stage of a gas turbine engine, the compressor stage having an inner and an outer casing, at least one rotating blade stage and at least one stator vane stage, the method comprising the steps of:
- forming a secondary annular airflow path within the compressor stage by extending a secondary annular member axially forward from a location axially aft of the at least one stator vane stage to a location adjacent a tip end of the at least one rotating blade stage;
- and
- capturing bleed air from adjacent the tip end of the at least one rotating blade stage in the secondary annular airflow path;
- wherein said step of forming includes the steps of:
- attaching a forward portion of the secondary annular member to the at least one rotating blade stage and attaching an aft portion of the secondary annular member to the at least one stator vane stage;
- inhibiting air leakage between the forward and aft portions of the secondary annular member by positioning a seal means between the forward and aft portions.
A method for obtaining bleed air at a preselected pressure from a compressor stage of a gas turbine engine, the compressor stage having an inner and an outer casing, at least one rotating blade stage and at least one stator vane stage, the method comprising the steps of:
- forming a secondary annular airflow path within the compressor stage by extending a secondary annular member axially forward from a location axially aft of the at least one stator vane stage to a location adjacent a tip end of the at least one rotating blade stage;
- and
- capturing bleed air from adjacent the tip end of the at least one rotating blade stage in the secondary annular airflow path;
- wherein the preselected pressure is determined by the steps:
- clipping a tip end of each blade of the at least one rotating blade stage on an axially aft corner thereof for forming a cutaway portion;
- and
- extending the secondary annular member into the cutaway portion for obtaining bleed air at a preselected pressure.
A method for obtaining bleed air at a preselected pressure from a compressor stage of a gas turbine engine, the compressor stage having an inner and an outer casing, at least one rotating blade stage and at least one stator vane stage, the method comprising the steps of:
- forming a secondary annular airflow path within the compressor stage by extending a secondary annular member axially forward from a location axially aft of the at least one stator vane stage to a location adjacent a tip end of the at least one rotating blade stage;
- and
- capturing bleed air from adjacent the tip end of the at least one rotating blade stage in the secondary annular airflow path;
- adjusting the camber of each blade of the at least one rotating blade stage for establishing a preselected air pressure at the blade tip end.
A method for obtaining bleed air at a preselected pressure from a compressor stage of a gas turbine engine, the compressor stage having an inner and an outer casing, at least one rotating blade stage and at least one stator vane stage, the method comprising the steps of:
- forming a secondary annular airflow path within the compressor stage by extending a secondary annular member axially forward from a location axially aft of the at least one stator vane stage to a location adjacent a tip end of the at least one rotating blade stage;
- and
- capturing bleed air from adjacent the tip end of the at least one rotating blade stage in the secondary annular airflow path;
- reducing the entry area between the outer casing and the secondary annular member for establishing a preselected pressure of the captured air.
Dependencies are inferred from the claim text.