WO2010002296A1 - Composant de turbine à gaz - Google Patents

Composant de turbine à gaz Download PDF

Info

Publication number
WO2010002296A1
WO2010002296A1 PCT/SE2008/000434 SE2008000434W WO2010002296A1 WO 2010002296 A1 WO2010002296 A1 WO 2010002296A1 SE 2008000434 W SE2008000434 W SE 2008000434W WO 2010002296 A1 WO2010002296 A1 WO 2010002296A1
Authority
WO
WIPO (PCT)
Prior art keywords
cooling air
gas turbine
outer casing
turbine engine
hub
Prior art date
Application number
PCT/SE2008/000434
Other languages
English (en)
Inventor
Sonny Andersson
Per WIDSTRÖM
Hans MÄRTENSSON
Original Assignee
Volvo Aero Corporation
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 Volvo Aero Corporation filed Critical Volvo Aero Corporation
Priority to PCT/SE2008/000434 priority Critical patent/WO2010002296A1/fr
Publication of WO2010002296A1 publication Critical patent/WO2010002296A1/fr

Links

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
    • F01D9/00—Stators
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a gas turbine engine component for a gas turbine engine for an aircraft, the component comprising an annular outer casing and a hub located radially inwards in relation to the outer casing, a gas flow passage being located between the outer casing and the hub, a plurality of circumferentially distributed struts extending between the outer casing and the hub, at least one of the struts presenting an inner cooling passage for a cooling air flow.
  • the invention also relates to a system for cooling of at least one strut in a gas turbine engine.
  • structural struts extend between an outer casing and a hub through a gas flow passage guiding hot combustion gases.
  • the struts can be cooled by an air flow through an inner cooling passage extending between an inner and an outer end of the respective strut; see for example US6860716B2.
  • Such a cooling air flow can be provided by bleeding air at an upstream compressor assembly, guiding it past a combustion chamber assembly to the turbine assembly, and allowing portions of it through the respective inner cooling passages in the struts.
  • Other portions of the cooling air might be allowed into respective cavities externally of the struts.
  • Such cavities are delimited by the struts and fairings surrounding the struts.
  • the fairings form delimitations of the passage for the flow of combustion gases, and are often referred to as vanes.
  • Bleeding air from the compressor decreases the engine efficiency. It is therefore important to not bleed more air than necessary for its purposes. It is difficult at a design stage of an engine to design cavities for the cooling air for the struts so as to obtain a cooling flow that is sufficient for the cooling purposes and not too large so as to cause unnecessary engine efficiency penalties. A further complicating factor is that with engine wear, specially with wear of seals and clearances in the engine, the thermal environment in the engine, specially in the turbine assembly, will change, and this change might also affect the cooling of the struts.
  • a gas turbine engine component of the kind mentioned initially comprising cooling air control means adapted to adjust the cooling air flow in the inner cooling passage.
  • the cooling air flow in the struts can be adjusted at any time during the life of the engine. This will make the design of the engine, as well as engine wear, considerably less critical for the desired balance between sufficient strut cooling and engine efficiency.
  • a system for cooling of at least one strut in a gas turbine engine comprising an annular outer casing and a hub located radially inwards in relation to the outer casing, a gas flow passage being located between the outer casing and the hub, the strut extending between the outer casing and the hub, and presenting an inner cooling passage for a cooling air flow, characterized in that it comprises cooling air control means for adjusting the cooling air flow in the inner cooling passage, and actuation means adapted to adjust the cooling air control means.
  • the cooling air flow in the struts can be adjusted at any time during the operation of the engine.
  • in-flight adjustments of the cooling air flow can be performed, so as to adapt the cooling air flow to different operational situations of the engine, e.g. take-off or cruise.
  • the overall fuel consumption can be reduced significantly.
  • active control of the air control means in operation the cooling air flow can be adjusted to follow the thermal load, resulting in lower coolant flow at conditions when the fuel consumption is critical, such as in cruise.
  • the cooling air flow can be adjusted based on conditions for a particular flight. For example, at take-off, the cooling requirements would differ depending on the atmosphere temperature and the elevation of the airport.
  • the cooling air flow can be adjusted based on inputs from sensors for atmosphere temperature and/or pressure temperature.
  • the actuation means can be controlled by a person, for example remotely from the cockpit in an aircraft.
  • a control unit can adapted to control the actuation means based at least partly on a temperature in the gas turbine engine.
  • the system can comprise a temperature sensor, the control unit being adapted to receive from the temperature sensor signals corresponding to the temperature.
  • Temperature sensor can for example be located in the cooling passage or downstream in relation to the cooling passage of the strut.
  • the system can further comprise a thermostat including at least one of the at least one valve and the actuation means.
  • - fig. 1 shows a schematic sectional view of an upper half of a gas turbine engine component, with the section following a central axis of the component,
  • - fig. 2 shows a view corresponding to the one shown in fig. 1, with an additional part
  • - fig. 3 shows a view corresponding to the one shown in fig. 1, of a gas turbine engine component according to an alternative embodiment of the invention
  • - fig. 4 shows a view corresponding to the one shown in fig. 1, depicting a further embodiment of the invention
  • - fig. 5 shows a view corresponding to the one shown in fig. 1, depicting a yet another embodiment of the invention.
  • Fig. 1 shows a schematic sectional view of an upper half of a generally circular gas turbine engine component 1, with the section following a central axis A of the component 1.
  • the component 1 forms a stationary part of a gas turbine engine, more particularly, a turbine assembly of such an engine.
  • the engine also comprises a rotational part 2, in turn including a shaft 201 and a turbine rotor 202 fixed thereto.
  • the engine can comprise any number of shafts 201, for example one, two or three shafts.
  • the rotational part 2 is centered on the stationary component 1 by means of bearings 3 so that the central axis A coincides with the rotational axis for the rotational part 2.
  • the stationary component 1 comprises an annular outer casing 101 and a hub 102 located radially inwards in relation to the outer casing 101, and a plurality of circumferentially distributed structural struts 103 extending between the outer casing 101 and the hub 102.
  • the section in fig. 1 is oriented along a longitudinal axis of one of the struts 103.
  • Each strut 103 is surrounded by a fairing 104, forming a delimitation of a gas flow passage 105 being located between the outer casing 101 and the hub 102, and presenting a generally annular shape.
  • the fairings 104 in the art often referred to as vanes, are located upstream of blades 203 of the turbine rotor 202, which might be a part of a low pressure turbine of the engine, a high pressure turbine being located upstream of the component 1.
  • the fairings 104 protect the struts 103 from hot combustion gases in the gas flow passage 105. However, a cooling arrangement is also provided to protect the struts 103 from elevated temperatures.
  • Each strut 103 presents an inner cooling passage 106 for a cooling air flow, illustrated with an arrow numbered 107.
  • the inner cooling passage 106 extends in a longitudinal direction of the strut 103, between an inner and an outer end of it.
  • the cooling air flow 107 is provided from a bleed air flow, indicated with an arrow numbered 108, provided in an outer cooling channel 109 from an upstream compressor assembly, (not shown).
  • the outer cooling channel 109 communicates via respective openings 110 at the outer ends of the respective struts 103 with the inner cooling passages 106.
  • Another opening 111 in one of the walls of the respective strut 103 allows communication between the inner cooling passage 106 and respective cavities 112 externally of the struts 103 and inside the fairings 104.
  • the opening 111 in the strut wall allows for a portion of the air flow entering the inner cooling passage 106 to enter said cavity 112 as indicated by an arrow numbered 113 being drawn partly with a broken line.
  • cooling air can be allowed to the cavity 112 without passing the inner cooling passage 106 of the strut 103, for example by direct communication between the cavity 112 and the outer cooling channel 109.
  • cooling air control means are provided comprising a valve 114 at the inner end of each strut 103.
  • valves 114 are provided at an outer portion of the hub 102.
  • the air flow is allowed to continue from the valves through openings 118 in a downstream wall of the hub, to be guided downstream in the engine.
  • the cooling air flow 107 is guided to the valve 114 via openings numbered 115 in fig. 1.
  • the valve 114 comprises a restriction device 116, the position of which in relation to an exit opening 117 is adjustable whereby the effective area of the flow path can be adjusted.
  • an access opening 119 in the outer wall of the outer casing 101 is provided.
  • a hand tool 120 can be seen with a handle 121 and an elongated element 122.
  • the restriction device 116 is in threaded engagement with a socket 123 and by turning the restriction device 116 it can move in a direction into or out of the exit opening 117.
  • the restriction device 116 is provided with an engagement arrangement 124 which is adapted to receive an end of the elongated element 122 of the hand tool 120 for engagement therewith.
  • a person can insert the elongated element 122 through the opening 119 in the outer wall of the outer casing 101, and through the opening 110 at the outer end of the strut 103, for engagement with the restriction device 116, whereupon the person can adjust the position of the restriction device 116 by turning the handle 121.
  • the valve 144 is accessible by a person by means of the hand tool from an external position in relation to the outer casing, for adjustment of the cooling air flow.
  • the adjustment of the restriction device 116 can be carried out at periodic service procedures of the engine.
  • the adjustment can be based on a diagnosis of the cooling of the struts 103, which diagnosis in turn can for example be based on a measurement of the temperature downstream of the struts, e.g. the engine exhaust temperature.
  • a deviation from a predetermined temperature value under certain operational conditions of the engine can indicate that the valves 114 have to be adjusted. More specifically, if the temperature is higher than the predetermined temperature value, the valves 114 need to be adjusted so as to increase the cooling air flow 107, and vice versa.
  • the diagnosis can be based on a measurement of the sealing capacity of the engine turbine blades, which measurement is known in itself in the art. Based on the sealing capacity of the engine turbine blades the temperature downstream of the struts can be determined.
  • the valve 114 comprises a restriction device 116 in the form of a shutter which is rotatably mounted on an axle 1161 so as to adjust the effective area of the flow path through the opening 118 in the downstream wall of the hub 102.
  • An elongated portion 122 in the form of a bolt is provided.
  • An inner end of the bolt 122 is in threaded engagement with the shutter 116 via a joint that allows relative rotational movement between the shutter 116 and the bolt 122.
  • At an outer end of the bolt its head is provided externally of the outer casing 101. Close to the head, the bolt 122 is connected to the outer casing via a joint that allows rotational movements of the bolt 122 in relation to the outer casing 101.
  • a person can engage a hand tool, in the form of a wrench, to the head of the bolt 122, whereupon the person can adjust the position of the shutter 116 by turning the bolt 122.
  • a system for cooling of the struts is provided.
  • An elongated element 122 is permanently situated in the strut 103, and is at its inner end connected to the restriction device 116.
  • the elongated element 122 extends through the outer casing 101, and is at its outer end connected to actuation means in the form of an electric stepping motor 131.
  • actuation means in the form of an electric stepping motor 131.
  • a separate opening 110 is provided for allowing air into the strut 103.
  • the restriction device 116 can be turned so that the cooling air flow 107 can be adjusted, similarly to what is described above with reference to fig. 1 and fig. 2.
  • a temperature sensor 132 is located downstream of the valve 114, more specifically downstream of the opening 118 in the downstream wall of the hub 102.
  • the temperature sensor 132 is electrically connected to an electronic control unit 133, as indicated by the broken line 134.
  • the engine control unit 133 electrically connected to the stepping motor 131, as indicated by the line 135, whereby it is adapted to control the stepping motor 131.
  • This control is carried out at least partly based on temperature values obtained by the temperature sensor 132.
  • adjustment of the restriction device 116 can be carried out on continuously during the engine operation, based on values from the sensor 132.
  • a deviation from a predetermined temperature value under certain operational conditions of the engine can indicate that the valves 114 have to be adjusted. More specifically, if the temperature is higher than the predetermined temperature value, the valves 114 need to be adjusted so as to increase the cooling air flow 107, and vice versa.
  • the electronic control unit 133 can be located in any suitable place in the engine, or in the aircraft on which the engine is mounted, and can of course be adapted to carry out numerous functions in addition to the valve control described here. It should also be noted that one temperature sensor 132 can be provided for controlling each valve 114 of the engine component 1, or alternatively, the control of a plurality of, or all, valves 114 can be carried out with one single temperature sensor 132.
  • the system for cooling of the struts comprises a thermostat T, located at an inner end of a respective of the struts 103.
  • the thermostat T depicted schematically in fig. 5 with components indicated with blocks, can be of any suitable type, for example of a bi-metal type. This means that the thermostat T comprises a valve 114 and actuation means 131, interacting in a manner known in itself, and not described here in detail.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention porte sur un composant de turbine à gaz qui comporte un boîtier externe annulaire (101) et un moyeu (102) situé radialement vers l'intérieur par rapport au boîtier externe (101), un passage d'écoulement de gaz (105) qui est situé entre le boîtier externe (101) et le moyeu (102), une pluralité d'entretoises (103) distribuées suivant la circonférence et s'étendant entre le boîtier externe (101) et le moyeu (102), au moins l'une des entretoises (103) présentant un passage de refroidissement interne (106) pour un écoulement d'air de refroidissement. Le composant comporte un moyen de commande d'air de refroidissement (114) conçu pour ajuster l'écoulement d'air de refroidissement dans le passage de refroidissement interne (106).
PCT/SE2008/000434 2008-07-04 2008-07-04 Composant de turbine à gaz WO2010002296A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/SE2008/000434 WO2010002296A1 (fr) 2008-07-04 2008-07-04 Composant de turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/SE2008/000434 WO2010002296A1 (fr) 2008-07-04 2008-07-04 Composant de turbine à gaz

Publications (1)

Publication Number Publication Date
WO2010002296A1 true WO2010002296A1 (fr) 2010-01-07

Family

ID=41466178

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/SE2008/000434 WO2010002296A1 (fr) 2008-07-04 2008-07-04 Composant de turbine à gaz

Country Status (1)

Country Link
WO (1) WO2010002296A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2938857A4 (fr) * 2012-12-29 2016-03-16 United Technologies Corp Bouclier thermique pour le refroidissement d'une entretoise
EP3099904A4 (fr) * 2014-01-28 2017-03-08 United Technologies Corporation Aube fixe pour cadre dans partie intermédiaire de turbine d'un moteur à réaction
US10107120B2 (en) 2012-01-30 2018-10-23 United Technologies Corporation Internal manifold for turning mid-turbine frame flow distribution
US10294819B2 (en) 2012-12-29 2019-05-21 United Technologies Corporation Multi-piece heat shield
US10378370B2 (en) 2012-12-29 2019-08-13 United Technologies Corporation Mechanical linkage for segmented heat shield
US10472987B2 (en) 2012-12-29 2019-11-12 United Technologies Corporation Heat shield for a casing
US11015471B2 (en) 2014-01-08 2021-05-25 Raytheon Technologies Corporation Clamping seal for jet engine mid-turbine frame

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3972181A (en) * 1974-03-08 1976-08-03 United Technologies Corporation Turbine cooling air regulation
US4416111A (en) * 1981-02-25 1983-11-22 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Air modulation apparatus
US5316437A (en) * 1993-02-19 1994-05-31 General Electric Company Gas turbine engine structural frame assembly having a thermally actuated valve for modulating a flow of hot gases through the frame hub
US6152685A (en) * 1997-12-08 2000-11-28 Mitsubishi Heavy Industries, Ltd. Seal active clearance control system for gas turbine stationary blade

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3972181A (en) * 1974-03-08 1976-08-03 United Technologies Corporation Turbine cooling air regulation
US4416111A (en) * 1981-02-25 1983-11-22 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Air modulation apparatus
US5316437A (en) * 1993-02-19 1994-05-31 General Electric Company Gas turbine engine structural frame assembly having a thermally actuated valve for modulating a flow of hot gases through the frame hub
US6152685A (en) * 1997-12-08 2000-11-28 Mitsubishi Heavy Industries, Ltd. Seal active clearance control system for gas turbine stationary blade

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10107120B2 (en) 2012-01-30 2018-10-23 United Technologies Corporation Internal manifold for turning mid-turbine frame flow distribution
EP2809920B1 (fr) * 2012-01-30 2019-07-31 United Technologies Corporation Collecteur interne permettant de tourner la distribution du flux d'un cadre de turbine intermédiaire
EP2938857A4 (fr) * 2012-12-29 2016-03-16 United Technologies Corp Bouclier thermique pour le refroidissement d'une entretoise
US9982561B2 (en) 2012-12-29 2018-05-29 United Technologies Corporation Heat shield for cooling a strut
US10294819B2 (en) 2012-12-29 2019-05-21 United Technologies Corporation Multi-piece heat shield
US10378370B2 (en) 2012-12-29 2019-08-13 United Technologies Corporation Mechanical linkage for segmented heat shield
US10472987B2 (en) 2012-12-29 2019-11-12 United Technologies Corporation Heat shield for a casing
US10941674B2 (en) 2012-12-29 2021-03-09 Raytheon Technologies Corporation Multi-piece heat shield
US11015471B2 (en) 2014-01-08 2021-05-25 Raytheon Technologies Corporation Clamping seal for jet engine mid-turbine frame
EP3099904A4 (fr) * 2014-01-28 2017-03-08 United Technologies Corporation Aube fixe pour cadre dans partie intermédiaire de turbine d'un moteur à réaction
US10669870B2 (en) 2014-01-28 2020-06-02 Raytheon Technologies Corporation Vane for jet engine mid-turbine frame

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