Closed-circuit air cooled turbine

• US 5,611,197 A
• Filed: 10/23/1995
• Issued: 03/18/1997
• Est. Priority Date: 10/23/1995
• Status: Expired due to Term

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Bunker, Ronald S.
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US08/551,870
• Time in Patent Office: 512 Days
• Field of Search: 60/39.07, 60/39.75, 60/266, 415/115, 415/117
• US Class Current: 60/806
• CPC Class Codes: F02C 7/185 Cooling means for reducing the temperature of the cooling air or gas
• CPC Class Codes: F02C 7/224 Heating fuel before feeding to the burner
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A gas turbine engine includes a compressor, combustor, and turbine, and a cooling air closed-circuit having an extraction line from the compressor to a hot turbine component such as vanes, blades, or shrouds, and a return line to the compressor. The extraction line may be joined to any suitable compressor stage for extracting air at a suitable pressure for flow to the turbine, with the return line being joined to any suitable injection stage of the compressor having a lower pressure than the extraction stage for driving the cooling air through the closed-circuit. The compressor itself therefore drives the closed-circuit and is self regulated.

Claims

1. A gas turbine engine comprising:

a compressor having an inlet for receiving air, stator vanes and rotor blades arranged in a plurality of stages for sequentially compressing said air, and an outlet for discharging said compressed air at maximum pressure;

a combustor disposed in flow communication with said compressor outlet for receiving said compressed outlet air;

means for mixing fuel with said compressed outlet air for undergoing combustion in said combustor and generating combustion gases therein;

a turbine disposed in flow communication with said combustor for receiving said combustion gases, and including stator vanes and rotor blades arranged in at least one stage for expanding said combustion gases to extract energy therefrom, said turbine blades being disposed radially within an annular shroud and extending radially outwardly from a rotor disk, said rotor disk being fixedly joined to said compressor;

a cooling air closed-circuit having an extraction line disposed in flow communication from an extraction stage of said compressor, for bleeding therefrom air at an extraction pressure, to a cooled component including one of said turbine vanes, blades, and shroud for internal cooling thereof, and having also a return line for returning spent cooling air from said cooled component to an injection stage of said compressor disposed upstream of said extraction stage, with said extraction stage having a greater pressure than that of said injection stage for driving said cooling air through said circuit and returning said spent cooling air into said compressor to rejoin said compressed air flowable therethrough;

said cooled component joined to said cooling circuit is hollow and includes at least one local cooling circuit without film cooling holes joined thereto for preventing discharge of said cooling air directly into said turbine;

a heat exchanger disposed in flow communication with said return line; and

means for channeling a cooling fluid through said heat exchanger for cooling said spent cooling air prior to return to said compressor.

2. An engine according to claim 1 wherein said heat exchanger is sized and configured so that said spent cooling air injected into said compressor matches in temperature said compressed air flowable therethrough at said injection stage.

3. A gas turbine engine comprising:

a compressor having an inlet for receiving air, stator vanes and rotor blades arranged in a plurality of stages for sequentially compressing said air, and an outlet for discharging said compressed air at maximum pressure;

a combustor disposed in flow communication with said compressor outlet for receiving said compressed outlet air;

means for mixing fuel with said compressed outlet air for undergoing combustion in said combustor and generating combustion gases therein;

a turbine disposed in flow communication with said combustor for receiving said combustion gases, and including stator vanes and rotor blades arranged in at least one stage for expanding said combustion gases to extract energy therefrom, said turbine blades being disposed radially within an annular shroud and extending radially outwardly from a rotor disk, said rotor disk being fixedly joined to said compressor;

a cooling air closed-circuit having an extraction line disposed in flow communication from an extraction stage of said compressor, for bleeding therefrom air at an extraction pressure, to a cooled component including one of said turbine vanes, blades, and shroud for internal cooling thereof, and having also a return line for returning spent cooling air from said cooled component to an injection stage of said compressor disposed upstream of said extraction stage, with said extraction stage having a greater pressure than that of said injection stage for driving said cooling air through said circuit and returning said spent cooling air into said compressor to rejoin said compressed air flowable therethrough;

said cooled component joined to said cooling circuit is hollow and includes at least one local cooling circuit without film cooling holes joined thereto for preventing discharge of said cooling air directly into said turbine; and

said cooling circuit is joined to said turbine blades.

4. A gas turbine engine comprising:

a compressor having an inlet for receiving air, stator vanes and rotor blades arranged in a plurality of stages for sequentially compressing said air, and an outlet for discharging said compressed air at maximum pressure;

a combustor disposed in flow communication with said compressor outlet for receiving said compressed outlet air;

means for mixing fuel with said compressed outlet air for undergoing combustion in said combustor and generating combustion gases therein;

a turbine disposed in flow communication with said combustor for receiving said combustion gases, and including stator vanes and rotor blades arranged in at least one stage for expanding said combustion gases to extract energy therefrom, said turbine blades being disposed radially within an annular shroud and extending radially outwardly from a rotor disk, said rotor disk being fixedly joined to said compressor;

a cooling air closed-circuit having an extraction line disposed in flow communication from an extraction stage of said compressor, for bleeding therefrom air at an extraction pressure, to a cooled component including one of said turbine vanes, blades, and shroud for internal cooling thereof, and having also a return line for returning spent cooling air from said cooled component to an injection stage of said compressor disposed upstream of said extraction stage, with said extraction stage having a greater pressure than that of said injection stage for driving said cooling air through said circuit and returning said spent cooling air into said compressor to rejoin said compressed air flowable therethrough.

said cooled component joined to said cooling circuit is hollow and includes at least one local cooling circuit without film cooling holes joined thereto for preventing discharge of said cooling air directly into said turbine; and

said cooling circuit is joined to said turbine shroud.