WO2020244690A1 - Refroidissement de turbine à gaz - Google Patents

Refroidissement de turbine à gaz Download PDF

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Publication number
WO2020244690A1
WO2020244690A1 PCT/DE2020/000111 DE2020000111W WO2020244690A1 WO 2020244690 A1 WO2020244690 A1 WO 2020244690A1 DE 2020000111 W DE2020000111 W DE 2020000111W WO 2020244690 A1 WO2020244690 A1 WO 2020244690A1
Authority
WO
WIPO (PCT)
Prior art keywords
valve device
adjustment range
cooling
actuator
adjusting
Prior art date
Application number
PCT/DE2020/000111
Other languages
German (de)
English (en)
Inventor
Christoph Lauer
Norman Cleesattel
Original Assignee
MTU Aero Engines AG
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of WO2020244690A1 publication Critical patent/WO2020244690A1/fr

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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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • 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 cooling system and a method for cooling at least one first turbine stage and at least one downstream second turbine stage of a gas turbine and a gas turbine, in particular aero-engine gas turbine, with the cooling system.
  • rotor blades rotate in a housing or a rotor in guide grids with guide vanes.
  • radial gaps should exist between elements rotating relative to one another. Such radial gaps can change during operation, in particular due to thermal factors.
  • turbine stages can be cooled by a cooling medium.
  • One object of an embodiment of the present invention is to improve a gas turbine and its operation. This problem is solved by a cooling system with the features of claim 1 ge. Claims 6, 7 provide a gas turbine with a cooling system described here and a method for cooling turbine stages of such a gas turbine under protection. Advantageous embodiments of the invention are the subject of the dependent claims. According to one embodiment of the present invention, a cooling system for cooling one or more first turbine stages and one or more downstream second turbine stages of a gas turbine, in particular aero-engine gas turbine,
  • CONFIRMATION COPY A first valve device which is connected to a single or multi-channel cooling medium and a first single or multi-channel cooling medium outlet for cooling the first turbine stage (s),
  • a second valve device which is connected to a single-channel or multi-channel cooling medium inlet and a second single-channel or multi-channel cooling medium outlet for cooling the second turbine stage (s), and
  • the or one or more of the first turbine stage (s) is / are in one embodiment (a) high-pressure turbine stage (s), the or one or more of the second turbine stage (s) in a further development (a) medium or low pressure turbine stage (s).
  • the or one or more first turbine stage (s) is (a) medium-pressure turbine stage (s), the or one or more second turbine stage (s) in a development (a) low - pressure turbine stage (s).
  • the present invention can be used for this purpose with particular advantage.
  • the first and second valve devices are connected to the same cooling medium inlet or are supplied with cooling medium through the same cooling medium inlet.
  • the cooling system can be made compact in one embodiment.
  • the first and second valve devices are connected to different cooling medium inlets or are supplied with cooling medium through different cooling medium inlets.
  • the turbine stages can be (even) more individually cooled in one version.
  • the cooling medium is gaseous, in particular (cooling) air.
  • the or one or both cooling medium inlet (s) with a single or multi-channel cooling medium withdrawal (point) is or are, in a further development connected to one or more compressor stage (s) of the gas turbine. In this way, particularly advantageous cooling can be implemented in one embodiment.
  • the first cooling medium outlet has one or more outlet openings and / or cooling spaces for cooling, in particular blowing, a one-part or multi-part housing of the first turbine stage (s).
  • the second cooling medium outlet has one or more outlet openings and / or cooling spaces for cooling, in particular blowing, a one-part or multi-part housing of the second turbine stage (s) in one embodiment.
  • the actuator has at least, in particular only, one, in one embodiment electrical or hydraulic, motor and / or actuator, and can in particular consist of this. As a result, the cooling system can be made more compact and / or light (er) in one embodiment.
  • the actuator actuates the first and / or second valve device mechanically or hydraulically or is set up for this purpose.
  • the actuator is configured to:
  • a second adjustment range which in one embodiment, in particular directly, adjoins the first adjustment range, in another embodiment is spaced or separated from the first adjustment range, for adjusting the standard cross section of the first valve device over or within a second adjustment range (s)
  • a standard cross-section of a valve device is a single-channel or multi-channel minimal flow-through or free cross-section of the valve device or is defined thereby. Its about the (ver) position of the actuator Define a value or values that change within an adjustment range or, in one embodiment, form an adjustment range of the valve device (via which the valve device is adjustable or is adjusted).
  • a standard cross-section of the second valve device in, in particular over the entire, second setting range at most 25%, in particular at most 15%, in one embodiment at most 5%, (s) of a maximum value in a particularly preferred embodiment the second valve device is closed in, in particular over the entire, second adjustment range.
  • the standard cross section of the second valve device in the first adjustment range has at least in sections at least 30%, in particular at least 50%, in one embodiment at least 75%, (s) of a maximum value.
  • a minimum value of the first adjustment range and a minimum value of the second adjustment range differ from one another by at most 50%, in one embodiment by a maximum of 25%, in particular by a maximum of 15%, in one embodiment by a maximum of 5%.
  • a maximum value of the first adjustment range and a maximum value of the second adjustment range differ from one another by at most 50%, in one embodiment by a maximum of 25%, in particular by a maximum of 15%, in one embodiment by a maximum of 5%.
  • At least one value of the first adjustment range and one value of the second adjustment range differ by a maximum of 10%, in one embodiment by a maximum of 5%, and in a further development not (at all) from one another.
  • a first value of the first adjustment range and a first value of the second adjustment range differ from one another by at most 10%, in one embodiment no more than 5%, in particular do not (at all) differ from one another, and a second value of the first differs Adjustment range and a second value of the second adjustment range by at most 10%, in one embodiment by at most 5%, differ from one another, in particular Not (at all) from one another; in a further development, at least one further value of the first adjustment range and another value of the second adjustment range (each) differ from one another by at most 10%, in one embodiment no more than 5%, in particular do not (at all) differ from one another or the first and second adjustment ranges in one embodiment have one, two or more (each) values that correspond to the adjustment ranges or differ by a maximum of 10%, in one embodiment a maximum of 5%.
  • the minimum value and the maximum value of the first adjustment range differ from one another, in particular by at least 10%, in one embodiment by at least 25%, in particular by at least 50%, of a maximum control cross-section of the first valve device, in a further development three or more values of the first adjustment range from one another.
  • the minimum value of the first adjustment range is equal to zero in one embodiment and greater than zero in another embodiment.
  • the maximum value of the first adjustment range is at least 30%, in particular at least 50%, in one embodiment at least 75%, of a maximum standard cross-section of the first valve device.
  • the minimum value and the maximum value of the second adjustment range differ from one another, in particular by at least 10%, in one embodiment by at least 25%, in particular by at least 50%, of a maximum control cross-section of the first valve device, in a further development three or more values of the second adjustment range from one another.
  • the minimum value of the second adjustment range is zero in one embodiment and greater than zero in another embodiment.
  • the maximum value of the second adjustment range is at least 30%, in particular at least 50%, in one embodiment at least 75%, of a maximum standard cross-section of the first valve device.
  • the second adjustment range corresponds - at least essentially - to the first adjustment range.
  • An embodiment of the present invention is thus based on the idea that the second valve device is open (more) in a first setting range and closed (more) in a second setting range and the first valve device is similar, preferably - at least essentially - the same or in both setting ranges Has identical adjustment ranges.
  • the first valve device can be regulated with one actuator when the second valve device is (more) open and the second valve device is (more) closed, in particular similarly.
  • the second valve device has a single-channel or multi-channel first passage and a cover with a single-channel or multi-channel second passage, which are controlled relative to one another by the actuator adjustable, in particular rotatable or displaceable, are or adjusted, in particular rotated or displaced, or are set up for this purpose, and define or limit a or the standard cross section of the second valve device.
  • the first valve device (also) has a single or multi-channel first passage and a cover with a single or multi-channel second passage, which can be adjusted, in particular rotated or displaced, relative to one another by the actuator are adjusted, in particular twisted or displaced, or are set up for this purpose, and define or limit the standard cross section of the first valve device.
  • a particularly advantageous, in particular more compact), light (right), reliable (right), simple (right) and / or precise (right) first or second valve device can be realized.
  • both aspects can advantageously be combined with one another.
  • the standard cross-sections or adjustment ranges according to the first aspect can be implemented particularly advantageously. Nevertheless, only the first or only the second aspect can be implemented (independently).
  • the first valve device has two concentric hollow cylinders, in one embodiment one of these hollow cylinders having the first passage of the first valve device and an inner one of these hollow cylinders, which in one embodiment rotatably rests against the outer hollow cylinder, has the second passage of the first valve device In another embodiment, conversely, an outer of these hollow cylinders has the second passage of the first valve device and an inner of these hollow cylinders, which in one embodiment rests rotatably on the outer hollow cylinder, has the first passage of the first valve device.
  • the second valve device has two concentric hollow cylinders, in one embodiment an outer one of these hollow cylinders the first passage of the second valve device and an inner one of these hollow cylinders, which in one embodiment rests rotatably on this outer hollow cylinder, the second passage the second valve device, in another embodiment, conversely, an outer one of these hollow cylinders has the second passage of the second valve device and an inner one of these hollow cylinders, which in one embodiment rests rotatably against this outer hollow cylinder, has the first passage of the second valve device.
  • the outer hollow cylinder of the first and second valve devices are connected to one another or formed in one piece. Additionally or alternatively, in one embodiment, the inner hollow cylinders of the first and second valve devices are connected to one another or formed in one piece.
  • a single-channel or multi-channel valve inlet of the first and / or second valve device is arranged on a jacket or end face of the (respective) outer hollow cylinder.
  • a single-channel or multi-channel valve outlet of the first and / or second valve device is arranged on a jacket or end face of the (respective) outer hollow cylinder.
  • first or second valve device in one embodiment, in particular in combination of two or more of these features, a particularly advantageous, in particular (still) combined compact (right), light (right), reliable (right), simple (right) and / or precise (right), first or second valve device can be realized.
  • the first and second valve devices have a common housing.
  • compact (re) actuation can be implemented in one embodiment.
  • the first and second valve devices have a common adjusting element which can be or is adjusted by the actuator and which changes the standard cross-section of the first and second valve device or is set up for this purpose.
  • the adjusting element can in particular have the inner or outer hollow cylinder.
  • the first and second valve devices have spaced apart housings and / or spaced apart adjusting elements, which are mechanically coupled via kinematics that can be adjusted or adjusted by the actuator and in one embodiment change or change the standard cross section of the respective valve device. are set up for this purpose.
  • the adjusting elements can in particular have the (respective) inner or outer hollow cylinder.
  • the actuator can advantageously be arranged in one embodiment.
  • first and second adjustment areas are designed in opposite directions or in opposite directions. Additionally or alternatively, in one embodiment the first and second adjustment areas adjoin one another, in particular directly or seamlessly.
  • first or second passage of the first valve device has (for this purpose) two oppositely directed or reversed, in particular mirror-symmetrical or reversed, formed and / or adjoining (directly or seamlessly) sections.
  • the first valve device can advantageously be adjusted and the second valve device can be closed (more).
  • the first and second valve devices are adjusted by the actuator in a first operating mode in or within the first setting range (s) and in a second operating mode in or within the second Stetl Scheme (s) adjusted.
  • the first operating mode is carried out at a higher ambient temperature (compared to the second operating mode), and the second operating mode at a lower ambient temperature (compared to the first operating mode).
  • the first valve device with the actuator advantageously controlled when the second valve device is (more) closed and thus in particular the ingress of rotor blades and / or guide blades of the second turbine stage is reduced and the efficiency of the gas turbine is improved.
  • first or second elements are referred to as first or second elements without loss of generality; in particular, the term “first” does not imply a more upstream arrangement and the term “second” does not imply a corresponding further (first) element.
  • one or more further (more upstream) turbine stages can be arranged between a combustion chamber of the gas turbine and the first turbine stage and / or the single or multi-channel second coolant outlet can be the only coolant outlet to (r cooling) the second tur- be binen level.
  • Upstream or downstream refers in the usual way to the direction of flow through the gas turbine, so that the downstream second turbine stage is closer to an outlet of the gas turbine than the first turbine stage.
  • FIG. 1 shows a gas turbine with a cooling system according to an embodiment of the present invention
  • FIG 3 shows a method for cooling a first and second turbine stage of the gas turbine according to an embodiment of the present invention.
  • FIG. 1 shows a gas turbine with a cooling system according to an embodiment of the present invention.
  • the gas turbine has a low pressure compressor 5, a high pressure compressor 4, a combustion chamber 3, a high pressure turbine with one or more first or high pressure turbine stage (s) 1 and a low pressure turbine with one or more second or low pressure turbine stage (s) 2.
  • the cooling system has a cooling medium inlet 30, which is supplied with cooling air by the low-pressure compressor 5, a first cooling medium outlet 31 to (r cooling) the or one or more of the first turbine stage (s) 1 and a second cooling medium outlet 32 (r Cooling) the or one or more of the second turbine stage (s) 2 on.
  • a first valve device has an inner hollow cylinder 11, which rests rotatably in an outer hollow cylinder 12.
  • a jacket surface of the outer hollow cylinder 12 has a valve inlet 13 of the first valve device, which forms a first passage of this valve device.
  • a jacket surface of the inner hollow cylinder 1 1 forms a cover with a second passage 14 of the first valve device.
  • the valve inlet 13 is connected to the cooling medium inlet 30, and an end-side valve outlet 15 of the first valve device is connected to the first cooling medium outlet 31.
  • a second valve device has an inner hollow cylinder 21 which rests rotatably in the outer hollow cylinder 12.
  • the jacket surface of the outer hollow cylinder 12 has a valve inlet 23 of the second valve device, which forms a first passage of this valve device.
  • a jacket surface of the inner hollow cylinder 21 forms a cover with a second passage 24 of the second valve device.
  • the valve inlet 23 is connected to the cooling medium inlet 30, and an end-side valve outlet 25 of the second valve device with the second cooling medium outlet 32.
  • a shaft of an actuator 40 which is controlled by a controller 41, rotates the inner hollow cylinders 1 1, 21 together in the common outer hollow cylinder 12.
  • the second passage 14 of the first valve device has two mirror-symmetrical sections 14A, 14B adjoining one another.
  • the second passage 24 of the second valve device only overlaps with the one section 14A.
  • FIG 3 shows a method for cooling the first and second turbine stages of the gas turbine according to an embodiment of the present invention.
  • the standard cross section of the second valve device is constant over a large part of the first adjustment range.
  • the passage 23 can be designed differently and thus an advantageous adjustment range of the second valve device can be realized.
  • the actuators of the first and second valve devices can be coupled via kinematics in a modification not shown.
  • A2 standard cross-section of the second valve device a first adjustment range

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)

Abstract

L'invention concerne un système de refroidissement pour refroidir au moins un premier étage (1) de turbine et au moins un deuxième étage (2) de turbine en aval d'une turbine à gaz, en particulier d'une turbine à gaz de groupe motopropulseur. Le système de refroidissement comporte : un premier dispositif de soupape, qui est relié à une entrée de liquide de refroidissement (30) et à une première sortie de liquide de refroidissement (31) menant au premier étage (1) de turbine ; un deuxième dispositif de soupape, qui est relié à une entrée de liquide de refroidissement (30) et à une deuxième sortie de liquide de refroidissement (32) menant vers le deuxième étage (2) de turbine ; et un actionneur (40) servant à ajuster le premier et le deuxième dispositif de soupape. L'actionneur (40) comporte une première zone de réglage (a) servant à ajuster une section transversale de régulation (A1) du premier dispositif de soupape sur une première zone d'ajustement lorsque le deuxième dispositif de soupape est ouvert, et une deuxième zone de réglage (b) se raccordant à la première zone de réglage (a) ou tenue à distance de celle-ci, servant à ajuster la section transversale de régulation (A1) du premier dispositif de soupape sur une deuxième zone d'ajustement. Une section transversale de régulation (A2) du deuxième dispositif de soupape présente dans la deuxième zone de réglage au maximum 25 % d'une valeur maximale, en particulier le deuxième dispositif de soupape est fermé dans la deuxième zone de réglage. Une valeur minimale de la première et de la deuxième zone d'ajustement diffèrent l'une de l'autre de 50 % au maximum et/ou une valeur maximale (A1max) de la première et de la deuxième zone d'ajustement diffèrent l'une de l'autre de 50 % au maximum et/ou au moins une valeur de la première et de la deuxième zone d'ajustement diffèrent l'une de l'autre de 10 % au maximum. Le deuxième dispositif de soupape comporte un premier passage (23) et/ou un recouvrement (21) pourvu d'un deuxième passage (24), qui peuvent être ajustés, en particulier tournés ou coulissés, l'un par rapport à l'autre par l'actionneur (40) et qui définissent une section transversale de régulation (A2) du deuxième dispositif de soupape.
PCT/DE2020/000111 2019-06-07 2020-05-27 Refroidissement de turbine à gaz WO2020244690A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102019208342.0A DE102019208342A1 (de) 2019-06-07 2019-06-07 Gasturbinenkühlung
DE102019208342.0 2019-06-07

Publications (1)

Publication Number Publication Date
WO2020244690A1 true WO2020244690A1 (fr) 2020-12-10

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Application Number Title Priority Date Filing Date
PCT/DE2020/000111 WO2020244690A1 (fr) 2019-06-07 2020-05-27 Refroidissement de turbine à gaz

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DE (1) DE102019208342A1 (fr)
WO (1) WO2020244690A1 (fr)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992011444A1 (fr) * 1990-12-22 1992-07-09 Rolls-Royce Plc Controle de jeu pour un moteur a turbine a gaz
EP2886805A1 (fr) * 2013-12-19 2015-06-24 Rolls-Royce plc Contrôle du jeu de l'extrémité d'une pale de rotor
DE102014217832A1 (de) * 2014-09-05 2016-03-10 Rolls-Royce Deutschland Ltd & Co Kg Kühlvorrichtung und Flugzeugtriebwerk mit Kühlvorrichtung

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3584458A (en) * 1969-11-25 1971-06-15 Gen Motors Corp Turbine cooling
FR2280791A1 (fr) * 1974-07-31 1976-02-27 Snecma Perfectionnements au reglage du jeu entre les aubes et le stator d'une turbine
US4329114A (en) * 1979-07-25 1982-05-11 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Active clearance control system for a turbomachine
FR2604750B1 (fr) * 1986-10-01 1988-12-02 Snecma Turbomachine munie d'un dispositif de commande automatique des debits de ventilation de turbine
DE102004011151B4 (de) * 2003-03-19 2015-11-26 Alstom Technology Ltd. Turbinenschaufel
US7717667B2 (en) * 2006-09-29 2010-05-18 General Electric Company Method and apparatus for operating gas turbine engines

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992011444A1 (fr) * 1990-12-22 1992-07-09 Rolls-Royce Plc Controle de jeu pour un moteur a turbine a gaz
EP2886805A1 (fr) * 2013-12-19 2015-06-24 Rolls-Royce plc Contrôle du jeu de l'extrémité d'une pale de rotor
DE102014217832A1 (de) * 2014-09-05 2016-03-10 Rolls-Royce Deutschland Ltd & Co Kg Kühlvorrichtung und Flugzeugtriebwerk mit Kühlvorrichtung

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