EP2503101A2 - System zur Regulierung einer Kühlflüssigkeit in einer Turbomaschine - Google Patents

System zur Regulierung einer Kühlflüssigkeit in einer Turbomaschine Download PDF

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Publication number
EP2503101A2
EP2503101A2 EP12160035A EP12160035A EP2503101A2 EP 2503101 A2 EP2503101 A2 EP 2503101A2 EP 12160035 A EP12160035 A EP 12160035A EP 12160035 A EP12160035 A EP 12160035A EP 2503101 A2 EP2503101 A2 EP 2503101A2
Authority
EP
European Patent Office
Prior art keywords
cooling fluid
header
cooling
stationary component
fluid
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP12160035A
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English (en)
French (fr)
Inventor
Sivaraman Vedhagiri
Don Conrad Johnson
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Priority claimed from US13/053,638 external-priority patent/US20110189000A1/en
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP2503101A2 publication Critical patent/EP2503101A2/de
Withdrawn legal-status Critical Current

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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00Stators
    • F01D9/06Fluid supply conduits to nozzles or the like
    • F01D9/065Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00Components
    • F05D2240/10Stators
    • F05D2240/12Fluid guiding means, e.g. vanes
    • F05D2240/127Vortex generators, turbulators, or the like, for mixing

Definitions

  • the present application relates generally to a cooling system on a turbomachine; and more particularly to, a system for regulating a cooling fluid within a wheelspace area of a turbomachine.
  • cooling fluid In some turbomachines, such as gas turbines, a portion of the air compressed by the compressor is typically diverted from combustion to cool various stationary and rotating components or to purge cavities within a gas turbine.
  • the diverted airflow (hereinafter “cooling fluid",) consumes a considerable amount of the total airflow compressed by the compressor.
  • the diverted cooling fluid is not combusted, reducing the performance of the gas turbine. Regulating and controlling the cooling fluid can dramatically increase the performance of the turbine.
  • the cooling fluid is extracted from the compressor, bypasses the combustion system, and flows through a cooling circuit.
  • the cooling circuit is typically located near various turbine components including the rotor compressor-turbine joint (hereinafter “marriage joint"), and various wheelspace areas.
  • the cooling circuit is typically integrated with a seal system. Relatively tight clearances may exist between the seal system components and the gas turbine rotor.
  • the seal system may include labyrinth seals located between rotating and stationary components.
  • the typical leakages that may occur through the labyrinth seal clearances are commonly used for cooling or purging areas downstream of the seals.
  • a high-pressure packing seal system HPPS
  • HPPS high-pressure packing seal system
  • the effectiveness of the cooling circuit is highly dependent on the performance of the HPPS.
  • the configuration of the cooling circuit determines whether or not adequate cooling fluid flows to the aforementioned turbine components.
  • the cooling circuit may include a chamber that directs the cooling fluid flow to a specific wheelspace area.
  • the system should adequately cool while improving the gas turbine efficiency.
  • the system should also provide for a deterministic flow through the cooling circuit.
  • the present invention resides in a system for regulating a cooling fluid, the system comprising: a gas turbine comprising: a combustion system that generates a working fluid; a compressor section comprising an inner barrel casing; a compressor discharge casing; and bypass chambers; wherein the cooling fluid flows through the inner barrel casing to the compressor discharge casing; a turbine section comprising rotating blades; diaphragms; nozzles; and wheelspace areas, wherein each wheelspace area comprises a series of rotating blades, a diaphragm, and a nozzle, and each bypass chamber allows the cooling fluid to flow from the compressor discharge casing to the wheelspace areas; and a nozzle cooling circuit substantially located within each stationary component, wherein the nozzle cooling circuit comprises a primary passage and a header; wherein a first end of the primary passage receives the cooling fluid and a second end of the primary passage is connected to header and the cooling fluid flows from the primary passage to the header; wherein the header comprises an upstream port and a downstream port that allows the cooling fluid to discharge
  • first, second, etc may be used herein to describe various elements, these elements should not be limited by these terms. These terms are only used to distinguish one element from another. For example, a first element could be termed a second element, and, similarly, a second element could be termed a first element, without departing from the scope of example embodiments.
  • the term "and/or" includes any, and all, combinations of one or more of the associated listed items.
  • the present invention may be applied to a variety of air-ingesting turbomachines. This may include, but is not limiting to, heavy-duty gas turbines, aero-derivatives, or the like. Although the following discussion relates to the gas turbine illustrated in FIG 1 , embodiments of the present invention may be applied to a gas turbine with a different configuration. For example, but not limiting of, the present invention may apply to a gas turbine with different, or additional, components than those illustrated in FIG. 1 .
  • FIG 1 is a schematic view, in cross-section, of a portion of a gas turbine, illustrating the environment in which an embodiment of the present invention operates.
  • a gas turbine 100 includes: a compressor section 105; a combustion section 150; and a turbine section 180.
  • the compressor section 105 includes a plurality of rotating blades 110 and stationary vanes 115 structured to compress a fluid.
  • the compressor section 105 may also include an extraction port 120, an inner barrel 125, a compressor discharge casing 130, a marriage joint 135, and a marriage joint bolt 137.
  • the combustion section 150 generally includes a plurality of combustion cans 155, a plurality of fuel nozzles 160, and a plurality of transition sections 165.
  • the plurality of combustion cans 155 may be coupled to a fuel source.
  • compressed air is received from the compressor section 105 and mixed with fuel received from the fuel source.
  • the air and fuel mixture is ignited and creates a working fluid.
  • the working fluid generally proceeds from the aft end of the plurality of fuel nozzles 160 downstream through the transition section 165 into the turbine section 180.
  • the turbine section 180 may include a plurality of rotating components 185; a plurality of stationary components 190, which include nozzles and diaphragms; and a plurality of wheelspace areas 195.
  • the turbine section 180 converts the working fluid to a mechanical torque.
  • a plurality of components experience high temperatures and may require cooling or purging. These components may include a portion of the compressor section 105, the marriage joint 135, and the plurality of wheelspace areas 195.
  • the extraction port 120 draws cooling fluid from the compressor section 105.
  • the cooling fluid bypasses the combustion section 150, and flows through a cooling circuit 200 (illustrated in FIG 2 ), for cooling or purging various components, including the marriage joint 135, and a plurality of wheelspace areas 195.
  • FIG 2 is a close-up view of the gas turbine illustrated in FIG 1 .
  • FIG 2 illustrates a non-limiting example of an embodiment of the cooling circuit 200.
  • the flow path of the cooling circuit 200 may start at the extraction port 120 (illustrated in FIG 1 ), flow through a portion of the compressor discharge casing 130, the inner barrel casing 125, and then a cavity at the aft end of the compressor section 105.
  • the cooling circuit 200 may reverse direction, flowing past the marriage joint 135, the seal system components 140, and to the wheelspace area 195.
  • FIG 3 illustrates a schematic view of the stationary component 190 of FIG 2 having a known nozzle cooling circuit.
  • the stationary component 190 comprises a nozzle cooling circuit 300 that is located internally.
  • the nozzle cooling circuit 300 allows the cooling fluid to cool the stationary component 190 from within.
  • the nozzle cooling circuit 300 receives the cooling fluid, illustrated in the FIGS by the arrows.
  • the currently known circuit 300 includes a path that may direct the cooling fluid to discharge on an upstream side of the stationary component 190. After exiting the stationary component 190, the cooling fluid may flow downstream through the seal system components 140 and then engage a downstream side of the stationary component 190.
  • FIG 4 illustrates a schematic view of a stationary component of FIG 2 having a nozzle cooling circuit, in accordance with an embodiment of the present invention.
  • the stationary component 190 comprises a nozzle cooling circuit 400 that is located internally.
  • the nozzle cooling circuit 400 allows the cooling fluid to cool the stationary component 190 in a more controlled and efficient way.
  • the nozzle cooling circuit 400 receives the cooling fluid which is illustrated in the FIGS by the arrows.
  • the cooling fluid flows from a primary passage 405 to a header 410; which allows the cooling fluid to discharge from the stationary component 190 in both upstream and downstream directions. This allows for a more efficient cooling of the downstream end of the stationary component 190.
  • FIG 5 illustrates an exploded schematic view of the stationary component of FIG 4 , in accordance with an embodiment of the present invention.
  • An embodiment of the nozzle cooling circuit 400 may comprise a primary passage 405, a header 410, a port 415, and a tuning plug 420.
  • An embodiment of the primary passage 405 may comprise a first end and a second end.
  • the first end may be positioned to receive the cooling fluid.
  • the second end located at an opposite end of the primary passage 405.
  • the second end may be connected to the header 410 in a manner that allows the cooling fluid to enter.
  • the nozzle cooling circuit 400 may comprise one primary passage 405.
  • the nozzle cooling circuit 400 may comprise multiple primary passages 405.
  • each primary passage 405 may comprise a dedicated header 410.
  • An embodiment of the header 410 may have the form of a through- hole, or the like. Each end of the header 410 may be enclosed via a cap 425, as illustrated, for example, in FIG 5 .
  • the cap 425 may be connected to the header 410, via welding, threaded connections, or other connection means.
  • the ports 415 may be considered an angled passage.
  • the ports 415 are angularly positioned relative to the header 410.
  • This angle 430 may induce a pre-swirl on the cooling fluid exiting each port 415 and entering the wheelspace area 195.
  • the angle 430 may comprise a range of from about 0 degrees to about 100 degrees, depending on the physical constraints associated with the associated components.
  • the pre-swirl allows the cooling fluid to flow in nearly the same direction and orientation as the rotating components 185 and the working fluid. This may improve the mixing of the cooling fluid with the working fluid, increasing the cooling efficiency.
  • the upstream ports 415 allows the cooling fluid to discharge the near an upstream end of the stationary component 190.
  • the downstream port 415 allows the cooling fluid to discharge near a downstream end of the stationary component 190.
  • the tuning plug 420 allows a user to control the flow of the cooling fluid exiting a designated port 415.
  • the tuning plug 420 comprises a through hole, or the like, which allows the cooling fluid to flow from the header 410 and discharge via a port 415.
  • the tuning plug 420 may assist the port 415 with directing the cooling fluid toward an outer surface of the stationary component 190.
  • the tuning plug 420 may adjust the mechanical properties of the cooling fluid exiting the nozzle cooling circuit 400. These properties may include, but are not limited to: velocity, flowrate, and pressure.
  • An embodiment of the tuning plug 420 may comprise a threaded connection that allows mating with the portion of the port 415.
  • An alternate embodiment of the tuning plug 420 may be press fit into the port 415.
  • Another alternate embodiment of the tuning plug 420 may comprise a variable internal diameter through which the cooling fluid discharges from the header 410, providing more control over the aforementioned properties.
  • FIG 6 illustrates a schematic view of the stationary component 190 of FIG 4 in use, in accordance with an embodiment of the present invention.
  • an embodiment of the present invention may function as follows.
  • the nozzle cooling circuit 400 receives the cooling fluid, represented in FIG 4 by the arrows.
  • the cooling fluid may flow through the primary passage 405.
  • the cooling fluid may enter the header 410.
  • the flow of the cooling fluid may diverge. A portion may flow towards the upstream port 415, discharging via the connected tuning plug 420. The remaining portion may flow towards the downstream port 415, discharging via the connected tuning plug 420.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP12160035A 2011-03-22 2012-03-19 System zur Regulierung einer Kühlflüssigkeit in einer Turbomaschine Withdrawn EP2503101A2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/053,638 US20110189000A1 (en) 2007-05-01 2011-03-22 System for regulating a cooling fluid within a turbomachine

Publications (1)

Publication Number Publication Date
EP2503101A2 true EP2503101A2 (de) 2012-09-26

Family

ID=45887981

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12160035A Withdrawn EP2503101A2 (de) 2011-03-22 2012-03-19 System zur Regulierung einer Kühlflüssigkeit in einer Turbomaschine

Country Status (2)

Country Link
EP (1) EP2503101A2 (de)
CN (1) CN102691532A (de)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3068996A4 (de) * 2013-12-12 2016-11-16 United Technologies Corp Mehrere einspritzlöcher für eine gasturbinenschaufel
EP3159486A1 (de) * 2015-10-20 2017-04-26 General Electric Company Radraumdurchflussmischkammer
EP3184749A1 (de) * 2015-10-20 2017-06-28 General Electric Company Radraumdurchflussmischkammer
EP3388638A1 (de) * 2017-04-11 2018-10-17 United Technologies Corporation Eitschaufelanordnung eines gasturbinenmotors
WO2020040747A1 (en) * 2018-08-21 2020-02-27 Siemens Aktiengesellschaft Modular casing manifold for cooling fluids of gas turbine engine
US10787920B2 (en) 2016-10-12 2020-09-29 General Electric Company Turbine engine inducer assembly

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9897318B2 (en) * 2014-10-29 2018-02-20 General Electric Company Method for diverting flow around an obstruction in an internal cooling circuit
ITUB20153103A1 (it) * 2015-08-13 2017-02-13 Ansaldo Energia Spa Gruppo turbina a gas con pre-vorticatore adattativo
US9970299B2 (en) * 2015-09-16 2018-05-15 General Electric Company Mixing chambers for turbine wheel space cooling

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US4666368A (en) * 1986-05-01 1987-05-19 General Electric Company Swirl nozzle for a cooling system in gas turbine engines
US5340274A (en) * 1991-11-19 1994-08-23 General Electric Company Integrated steam/air cooling system for gas turbines
ATE230065T1 (de) * 1996-06-21 2003-01-15 Siemens Ag Turbinenwelle sowie verfahren zur kühlung einer turbinenwelle
US8015824B2 (en) * 2007-05-01 2011-09-13 General Electric Company Method and system for regulating a cooling fluid within a turbomachine in real time
US7914253B2 (en) * 2007-05-01 2011-03-29 General Electric Company System for regulating a cooling fluid within a turbomachine

Non-Patent Citations (1)

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Title
None

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11053808B2 (en) 2013-12-12 2021-07-06 Raytheon Technologies Corporation Multiple injector holes for gas turbine engine vane
EP3068996A4 (de) * 2013-12-12 2016-11-16 United Technologies Corp Mehrere einspritzlöcher für eine gasturbinenschaufel
US10641117B2 (en) 2013-12-12 2020-05-05 United Technologies Corporation Multiple injector holes for gas turbine engine vane
EP3159486A1 (de) * 2015-10-20 2017-04-26 General Electric Company Radraumdurchflussmischkammer
EP3184749A1 (de) * 2015-10-20 2017-06-28 General Electric Company Radraumdurchflussmischkammer
US10125632B2 (en) 2015-10-20 2018-11-13 General Electric Company Wheel space purge flow mixing chamber
US10132195B2 (en) 2015-10-20 2018-11-20 General Electric Company Wheel space purge flow mixing chamber
US11846209B2 (en) 2016-10-12 2023-12-19 General Electric Company Turbine engine inducer assembly
US11466582B2 (en) 2016-10-12 2022-10-11 General Electric Company Turbine engine inducer assembly
US10787920B2 (en) 2016-10-12 2020-09-29 General Electric Company Turbine engine inducer assembly
EP3388638A1 (de) * 2017-04-11 2018-10-17 United Technologies Corporation Eitschaufelanordnung eines gasturbinenmotors
US10436050B2 (en) 2017-04-11 2019-10-08 United Technologies Corporation Guide vane arrangement for gas turbine engine
WO2020040747A1 (en) * 2018-08-21 2020-02-27 Siemens Aktiengesellschaft Modular casing manifold for cooling fluids of gas turbine engine
US11480055B2 (en) 2018-08-21 2022-10-25 Siemens Energy Global GmbH & Co. KG Modular casing manifold for cooling fluids of gas turbine engine

Also Published As

Publication number Publication date
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