EP2014871A2 - Systeme und Verfahren mit variablen Schaufeln - Google Patents

Systeme und Verfahren mit variablen Schaufeln Download PDF

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Publication number
EP2014871A2
EP2014871A2 EP08252364A EP08252364A EP2014871A2 EP 2014871 A2 EP2014871 A2 EP 2014871A2 EP 08252364 A EP08252364 A EP 08252364A EP 08252364 A EP08252364 A EP 08252364A EP 2014871 A2 EP2014871 A2 EP 2014871A2
Authority
EP
European Patent Office
Prior art keywords
vane
pressurized air
operative
throat area
turbine engine
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.)
Granted
Application number
EP08252364A
Other languages
English (en)
French (fr)
Other versions
EP2014871A3 (de
EP2014871B1 (de
Inventor
Michael G. Mccaffrey
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.)
RTX Corp
Original Assignee
United Technologies Corp
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
Application filed by United Technologies Corp filed Critical United Technologies Corp
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Publication of EP2014871A3 publication Critical patent/EP2014871A3/de
Application granted granted Critical
Publication of EP2014871B1 publication Critical patent/EP2014871B1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/148—Blades with variable camber, e.g. by ejection of fluid
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/17—Purpose of the control system to control boundary layer

Definitions

  • the invention relates to gas turbine engines.
  • Gas turbine engines use compressors to compress gas for combustion.
  • a compressor typically uses alternating sets of rotating blades and stationary vanes to compress gas. Gas flowing through such a compressor is forced between the sets and between adjacent blades and vanes of a given set. Similarly, after combustion, hot expanding gas drives a turbine that has sets of rotating blades and stationary vanes.
  • an exemplary embodiment of a gas turbine engine defining a gas flow path comprises: a first vane extending into the gas flow path and having: an interior operative to receive pressurized air; an outer surface; and outlet ports communicating between the outer surface and the interior of the first vane, the outlet ports being operative to receive the pressurized air from the interior and emit the pressurized air into the gas flow path such that a throat area defined, at least in part, by the first vane is modified.
  • An exemplary embodiment of a vane assembly comprises: a first vane having: an outer surface; an interior defining a cavity operative to receive pressurized air; and outlet ports communicating between the outer surface and the cavity, the outlet ports being operative to receive the pressurized air from the cavity and emit the pressurized air through the outer surface; and a valve assembly operative to regulate the pressurized air emitted by the first vane.
  • An exemplary embodiment of a method for modifying the throat area between vanes of a gas turbine engine comprises: directing a gas flow path of the gas turbine engine between a first vane and a second vane, wherein each of the first vane and the second vane has an outer surface and an interior; and emitting pressurized air from outlet ports communicating between the outer surface and the interior of the first vane, wherein the emitted pressurized air from the first vane modifies a throat area between the first vane and the second vane.
  • gas passing through a gas turbine engine enters a turbine that includes rotating blades and stationary vanes.
  • the gas, following the gas flow path is forced between adjacent vanes.
  • the vanes are often shaped like airfoils and, therefore, have aerodynamic properties similar to airfoils.
  • the flow of gas between adjacent vanes results in a throat area determined by, for example, the shape and relative position of the vanes.
  • the angle of the vanes relative to the gas flow path may be mechanically changed to vary the location and/or size of the throat area and alter the efficiency of the engine.
  • the gas turbine engine is configured as a turbofan.
  • FIG. 1 is a schematic side view illustrating an exemplary embodiment of a turbine section 100 of a gas turbine engine.
  • rotating blades 104 are attached to a disk that is rotated by a shaft 106.
  • Stationary vanes 108 are attached to the casing of the engine between the blades 104.
  • gas enters the turbine section along gas flow path 102 and drives the blades 104.
  • the gas exits the turbine section 100 along gas flow path 102.
  • FIG. 2 is a simplified, side cutaway view of vane assembly 200 that includes a vane airfoil 202 and a valve assembly 208. Note that vane airfoil 202 typically is mounted to and spans between an outer diameter vane platform and an inner diameter vane platform, neither of which is depicted in FIG. 2 .
  • valve assembly 208 includes a piston 204 and solenoid 220, which is used to actuate the piston.
  • Inlet ports 218 provide gas to the valve assembly so that actuation of the piston pressurizes the received gas.
  • Vane airfoil 202 includes an interior cavity 214 that receives pressurized air from the inlet ports via the piston, and outlet ports 216 that are used to emit the pressurized air into the gas flow path.
  • the gas emitted by the outlet ports 216 affects the throat area formed between vane airfoil 202 and an adjacent vane airfoil. This is in contrast to emission of pressurized gas from ports of a vane airfoil for performing film cooling.
  • the pressure of the pressurized gas emitted from the outlet ports 216 is greater than that used for performing film cooling.
  • the pressurized gas from the outlet ports 216 urges the gas flow path, which flows about the vane airfoil during operation of the gas turbine engine, away from the exterior surface of the vane airfoil to a greater extent than that caused by pressurized gas involved in film cooling.
  • the boundary layer formed by the film-cooling air also is urged away from the exterior of the vane airfoil.
  • the pressure of the gas required to alter the throat is not available from the compressor alone.
  • piston 204 is used in the embodiment of FIG. 2 to increase the pressure of the gas provided to the outlet ports. In other embodiments, various other mechanisms could be used to increase the gas pressure.
  • the shape of the vane assembly 200 illustrated in FIG. 2 is merely an illustration of but one possible embodiment.
  • the shape of the vane assembly 200 may vary depending on a variety of factors including, but not limited to, the component to which the vane assembly 200 is attached, the location of the vane assembly 200 in the gas turbine engine, the gas flow path around the vane assembly 200 at particular gas flow velocities, desired design characteristics of the gas turbine engine, and materials used in the fabrication of the gas turbine engine.
  • a controller 212 also is provided.
  • the controller 212 is used to open and close the valve assembly 208.
  • the valve assembly 208 is left open such that the outlet ports 216 emit a constant flow of pressurized air.
  • the valve assembly 208 may be opened and closed intermittently.
  • the pressurized air may be emitted from the outlet ports 216 in pulses.
  • operation in a pulsed mode allows the pressure of the pressurized air to increase prior to being emitted into a gas flow path.
  • the controller 212 may be set to control the frequency of the pulses of emitted pressurized air. Controlling the frequency of the pulses may be desirable because a change in the throat area based on a frequency of pulses may allow the aerodynamic characteristics of the engine to be adjusted.
  • the frequencies of the pulses may be controlled to modify one or more throat areas in a specific region of an engine to control local pressure ratios and/or local temperatures.
  • the pulse frequencies may also be timed to adjust for resonance in the engine that may result in vane and blade vibrations. These pulses may be used to add a canceling frequency that may effectively cancel engine resonance, for example.
  • FIG. 3 is a top cutaway view of a pair of vanes in an embodiment of a gas turbine engine. As shown in FIG. 3 , gas is forced between the vanes 300 along gas flow path 302, forming a throat area 304. The shape of the adjacent vanes 300, their proximity to each other, and the angle of incidence to the gas flow path 302 are possible factors that can influence the location and size of the throat area 304.
  • FIG. 4 depicts a top cutaway view of another embodiment of a vane assembly.
  • vanes 406 and 412 are adjacent vanes.
  • Vane 406 has an interior cavity 404 that is connected to a pressurized air source (not shown).
  • Outlet ports 410 are located on the surface of vane 406 and are in communication with interior cavity 404.
  • Pressurized air emitted from the outlet ports 410 in vane 406 defines a boundary layer 408 that has an aerodynamic effect on the gas flow path 402.
  • the boundary layer 408 associated with the pressurized air from the outlet ports modifies the location and/or size of the throat area 416, and may, for example, move it upstream.
  • the outlet ports of this embodiment are oriented such that the flow from the outlet ports is generally in a direction of the gas flow path. In other embodiments, however, the orientation can be different, such as by providing a perpendicular (see FIG. 5 ) or counter flow (not shown).
  • Modifying the throat area of an engine may affect the flow of gases through the engine. For instance, such modifying can affect the pressure ratio of the compressor and change the relationship between the flow and the pressure ratio. For example, a lower flow rate can increase the pressure ratio.
  • FIG. 5 depicts a top cutaway view of another embodiment of a vane assembly.
  • vane assembly 500 incorporates two adjacent vanes, a first vane 501 and a second vane 503.
  • the first vane 501 and the second vane 503 are spaced from each other to define a gas flow path 502.
  • the first vane 501 includes three chambers - a film-cooling chamber 504, a suction side chamber 505 and a pressure side chamber 507.
  • the film-cooling chamber 504, suction side chamber 505 and the pressure side chamber 507 include ports, such as ports 506, 509 and 511, respectively.
  • the film-cooling chamber 504 receives cooling pressurized air that is emitted from the associated ports, e.g., port 506.
  • This air creates a relatively thin boundary layer 530 that is located adjacent to the exterior of the vane 501 to serve as a barrier against the hot gas flowpath 502.
  • the suction side chamber 505 and the pressure side chamber 507 also receive pressurized air, which is at a higher pressure than that provided to chamber 504, that is emitted from associated ports, e.g., ports 509 and 511.
  • the pressurized air emitted from chamber 507 creates a boundary layer 513 along the pressure surface 515 of the first vane 501 that affects the throat area 550.
  • the boundary layer 513 tends to urge the boundary layer 530 away from the pressure surface 515, thereby causing the boundary layer 530 to dissipate and mix with the gas of the gas flow path 502.
  • the second vane 503 also includes three chambers - a film-cooling chamber 532, a suction side chamber 510 and a pressure side chamber 512.
  • the film-cooling chamber 532, suction side chamber 510 and the pressure side chamber 512 include ports, such as ports 534, 522 and 514, respectively.
  • the film-cooling chamber 532 receives cooling pressurized air that is emitted from the associated ports, e.g., port 534.
  • This air creates a relatively thin boundary layer 536 that is located adjacent to the exterior of the vane 503.
  • the suction side chamber 510 and the pressure side chamber 512 also receive pressurized air, which is at a higher pressure than that provided to chamber 534, that is emitted from associated ports, e.g., ports 522 and 514.
  • the pressurized air emitted from chamber 510 creates a boundary layer 525 along the suction surface 508 of the vane 503 that affects the throat area 550.
  • the boundary layer 525 tends to urge the boundary layer 536 away from the suction surface 508, thereby causing the boundary layer 536 to dissipate and mix with the gas of the gas flow path 502.
  • the suction side chambers 505 and 510 and the pressure side chambers 507 and 512 may be separate and unconnected to each other so that the air emitted from each of the chambers may be controlled independently.
  • the suction side chambers 505 and 510 and the pressure side chambers 507 and 512 may be in communication, and therefore, dependently controlled.

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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)
  • Supercharger (AREA)
  • Control Of Turbines (AREA)
EP08252364A 2007-07-10 2008-07-10 Systeme und Verfahren mit variablen Schaufeln Expired - Fee Related EP2014871B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/775,523 US20090016871A1 (en) 2007-07-10 2007-07-10 Systems and Methods Involving Variable Vanes

Publications (3)

Publication Number Publication Date
EP2014871A2 true EP2014871A2 (de) 2009-01-14
EP2014871A3 EP2014871A3 (de) 2011-08-31
EP2014871B1 EP2014871B1 (de) 2012-11-14

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EP08252364A Expired - Fee Related EP2014871B1 (de) 2007-07-10 2008-07-10 Systeme und Verfahren mit variablen Schaufeln

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EP (1) EP2014871B1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8573946B2 (en) 2009-06-22 2013-11-05 Rolls-Royce Plc Compressor blade
WO2014133612A1 (en) * 2013-02-26 2014-09-04 Bloxham Matthew J Gas turbine engine variable geometry flow component
CN109477417A (zh) * 2016-12-21 2019-03-15 三菱重工发动机和增压器株式会社 涡轮增压器、涡轮增压器的喷嘴叶片以及涡轮机
WO2020236329A1 (en) * 2019-05-17 2020-11-26 Solar Turbines Incorporated Nozzle segment

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8197209B2 (en) * 2007-12-19 2012-06-12 United Technologies Corp. Systems and methods involving variable throat area vanes
US20120304660A1 (en) 2011-06-06 2012-12-06 Kupratis Daniel B Turbomachine combustors having different flow paths
US9560630B2 (en) * 2011-08-12 2017-01-31 Qualcomm Incorporated Devices for reduced overhead paging
US10221720B2 (en) * 2014-09-03 2019-03-05 Honeywell International Inc. Structural frame integrated with variable-vectoring flow control for use in turbine systems
US10641113B2 (en) * 2015-04-08 2020-05-05 United Technologies Corporation Airfoils
US9957900B2 (en) * 2015-05-11 2018-05-01 General Electric Company System and method for flow control in turbine
US10711702B2 (en) 2015-08-18 2020-07-14 General Electric Company Mixed flow turbocore
US10578028B2 (en) 2015-08-18 2020-03-03 General Electric Company Compressor bleed auxiliary turbine
US20170051680A1 (en) * 2015-08-18 2017-02-23 General Electric Company Airflow injection nozzle for a gas turbine engine
US10760426B2 (en) * 2017-06-13 2020-09-01 General Electric Company Turbine engine with variable effective throat
US20210301684A1 (en) * 2020-03-30 2021-09-30 General Electric Company Fluidic flow control device
US11692448B1 (en) 2022-03-04 2023-07-04 General Electric Company Passive valve assembly for a nozzle of a gas turbine engine

Citations (1)

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EP0164539A1 (de) 1984-05-15 1985-12-18 A. S. Kongsberg Väpenfabrikk Gasturbine mit veränderlicher Strömung

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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8573946B2 (en) 2009-06-22 2013-11-05 Rolls-Royce Plc Compressor blade
WO2014133612A1 (en) * 2013-02-26 2014-09-04 Bloxham Matthew J Gas turbine engine variable geometry flow component
US9617868B2 (en) 2013-02-26 2017-04-11 Rolls-Royce North American Technologies, Inc. Gas turbine engine variable geometry flow component
CN109477417A (zh) * 2016-12-21 2019-03-15 三菱重工发动机和增压器株式会社 涡轮增压器、涡轮增压器的喷嘴叶片以及涡轮机
CN109477417B (zh) * 2016-12-21 2021-12-24 三菱重工发动机和增压器株式会社 涡轮增压器、涡轮增压器的喷嘴叶片以及涡轮机
WO2020236329A1 (en) * 2019-05-17 2020-11-26 Solar Turbines Incorporated Nozzle segment

Also Published As

Publication number Publication date
EP2014871A3 (de) 2011-08-31
US20090016871A1 (en) 2009-01-15
EP2014871B1 (de) 2012-11-14

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