EP0393531A1 - Dispositif pour la variation du calage des aubes de stator - Google Patents

Dispositif pour la variation du calage des aubes de stator Download PDF

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Publication number
EP0393531A1
EP0393531A1 EP90107101A EP90107101A EP0393531A1 EP 0393531 A1 EP0393531 A1 EP 0393531A1 EP 90107101 A EP90107101 A EP 90107101A EP 90107101 A EP90107101 A EP 90107101A EP 0393531 A1 EP0393531 A1 EP 0393531A1
Authority
EP
European Patent Office
Prior art keywords
expansion
lever
rod
support housing
adjusting
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
EP90107101A
Other languages
German (de)
English (en)
Other versions
EP0393531B1 (fr
Inventor
Joachim Popp
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.)
MTU Aero Engines AG
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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 Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Publication of EP0393531A1 publication Critical patent/EP0393531A1/fr
Application granted granted Critical
Publication of EP0393531B1 publication Critical patent/EP0393531B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/20—Devices dealing with sensing elements or final actuators or transmitting means between them, e.g. power-assisted
    • 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
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line

Definitions

  • the invention relates to a device for adjusting guide vanes in a turbo engine by means of the thermal expansion of an expansion rod which is acted upon by working gas, which is fixed at one end in a fixed position on a support housing and is articulated at its other end to the short lever arm of a transmission lever pivotally fastened in the support housing.
  • the arrangement according to the invention has the essential advantage that a direct adjustment of the guide vanes can be carried out without connecting an external control loop. This results in both shorter response times and a lower risk of system errors.
  • the adjustment is purely mechanical and is therefore advantageously independent of electrical, hydraulic or other components.
  • the arrangement is characterized by an exceptionally simple construction.
  • the long lever arm of the transmission device designed as a transmission lever is connected to the adjusting ring by a connecting shaft which is articulated in a similar manner, the connecting shaft being able to be made of the same material as the expansion rod and thus also functioning as an expansion rod.
  • the connecting shaft does not have the same effect as the primary expansion rod, since its change in length cannot be multiplied by the translation factor of the translation lever. It is possible to design the translation device as a one- or two-armed lever or as meshing gears.
  • the expansion rod preferably has stiffening ribs to prevent buckling, which at the same time increases its surface area and allows faster heating or cooling.
  • Such longitudinal stiffening ribs can also be attached to the connecting shaft.
  • the transmission lever is preferably designed with one arm and aligned radially in the support housing or in the turbo engine.
  • the pivot point of the transmission lever can be provided outside or inside, depending after which solution causes less weight or is structurally easier to implement.
  • the expansion rod is flushed with working gas. Rooms that are permanently flowed through by this working gas are particularly suitable for this. B. blow-off rooms of compressors for cooling or sealing air - because due to the high heat transfer medium flowing medium / expansion rod short reaction times can be achieved. It is also possible to provide suitable baffles through which the air blown off by the compressor is led directly to the expansion rod and which can also advantageously shorten the reaction times.
  • the device is coupled to a plurality of adjusting rings of different compressors or compressor stages.
  • the adjustable guide vane stages located one behind the other generally have to be adjusted synchronously if there has been a shift in the compressor operating point.
  • One possibility of coupling different adjusting rings is to connect them via a rotatable shaft, which shaft can be articulated either directly on the transmission lever or indirectly on the adjusting ring coupled to the transmission lever.
  • An alternative coupling option is that several adjusting rings are coupled via a common push rod, an adjusting lever with a defined transmission ratio of its lever arms being provided between each adjusting ring and the push rod. This makes it possible to control each vane stage according to its individual flow specifications. It is also possible to design the shaft or the push rod to be flexible, in order to be able to transmit the adjustment movement even when the housing specifications are unfavorable per se.
  • the expansion rod or the connecting shaft it is necessary for the expansion rod or the connecting shaft to have a significantly different coefficient of thermal expansion than the surrounding support housing.
  • the expansion coefficient of the expansion rod can be significantly larger or also significantly lower than that of the support housing. It has been shown that the ratio of the two coefficients of linear expansion should be at least 2, with significantly larger values being achievable by suitable choice of material.
  • Preferred materials for the support housing are, for example, X10, 17-4 PH, which have an ⁇ of approximately 11 ⁇ 10 ⁇ 61 / grd. EPC10 or INCO 904 with an ⁇ of approx. 4 ⁇ 10 ⁇ 61 / grd is suitable as material for the expansion rod. It is also conceivable to manufacture the expansion rod from a ceramic, in particular a fiber-reinforced ceramic, since this material also has an extremely low expansion coefficient of less than 4 ⁇ 10 ⁇ 61 / grd.
  • a further advantageous embodiment provides that the device is arranged in the region of a high-pressure compressor and is coupled to adjusting rings of a low-pressure compressor via a push rod or shaft.
  • the device is arranged in the region of a high-pressure compressor and is coupled to adjusting rings of a low-pressure compressor via a push rod or shaft.
  • the front stages of a compressor in particular the stages of a low-pressure compressor, are equipped with adjustable guide blades, while the last rows of blades of a high-pressure compressor have only rigid guide blades.
  • air is often branched off as sealing air or cooling air in the area of the last high-pressure compressor stages, so that it is suitable to arrange the adjusting device according to the invention in the area of the high-pressure compressor.
  • the invention can be arranged in the context of axial compressors, radial compressors or combined axial and radial compressors, with a coupling of the guide vanes of the radial and axial compressor also making sense. It is also possible for the invention in the context of the door Use the vane guide vane adjustment, whereby the expansion rod is preferably supplied with working gas which is branched off behind the turbine stage.
  • the transmission lever is articulated with its pivot point in the support housing, as a result of which the thermally induced rotation angle of the adjusting ring results from the change in length of the expansion rod relative to the support housing, multiplied by the transmission ratio of the transmission lever.
  • An alternative embodiment of the invention provides that the transmission lever is articulated directly on the adjusting ring and two expansion rods attached to it at one end are articulated thereon. In this embodiment, two expansion rods are provided, which results in a larger angle of rotation of the adjusting ring with otherwise the same parameters. It is possible to manufacture both expansion rods with approximately the same coefficient of linear expansion, i. that is, both are made of the same material. In this case, the expansion rods will be arranged on both sides of the transmission lever. Alternatively, it is also possible to use two expansion rods with significantly different coefficients of linear expansion. In this case, both expansion rods will be arranged on the same side of the transmission lever.
  • a further advantageous embodiment of the invention provides that the pivot point of the fixedly articulated end of the torsion bar can be displaced relative to the support housing in the direction of expansion by means of an adjusting motor.
  • This makes it possible to carry out an overlapping adjustment of the guide vanes independently of the temperature-controlled adjustment, for example via the electronic engine control unit. It is also possible, instead of changing the fixed pivot point of the torsion bar, to make the pivot point of the transmission lever movable.
  • the adjustment motor can be carried out hydraulically, pneumatically or electrically.
  • FIG. 1 In the cross section shown in FIG. 1 through the compressor of a turbo engine, a compressor rotor 1 can be seen, on which radially oriented compressor blades 2 distributed over the circumference are attached.
  • the pivoting of the guide vanes 5 is achieved in that they are connected to pivot levers 6, which in turn are movably mounted in a circumferentially rotatable adjusting ring 7 in several degrees of freedom.
  • the adjusting ring 7 is mounted on the housing 4 by means of guide rails 8, which can also be supported by rollers for damping friction.
  • the adjustment of the adjusting ring 7 by the gas temperature occurs in that an expansion rod 9 is attached at one end to a support housing 10 by means of a swivel joint 12, and is articulated at its other end to a transmission lever 11.
  • the translation lever 11 is rotatably mounted with its pivot point 13 in the support housing 10. It has a short lever arm k to the articulation point of the expansion rod 9 and a long lever arm l to the articulation point of a connecting shaft 14.
  • the ratio l / k should preferably be greater than 3.
  • the connecting shaft 14 serves to couple the adjusting ring 7 to the transmission lever 11.
  • the inventive adjustment of the guide vanes 5 by hot gas takes place in that 4 working gas can pass from the flow channel 3 into the outer space 17 via openings 16 in the flow channel wall.
  • the expansion rod 9 is heated to the working gas temperature, whereby it assumes a length defined by its coefficient of linear expansion.
  • the support housing 10 is heated by the working gas, but a different thermal expansion from the expansion rod 9 occurs because the support housing 10 has a substantially different coefficient of linear expansion.
  • the working gas located outside is preferably passed on for cooling turbine components, as sealing air for sealing the storage chamber or for ventilation of the cabin.
  • a shaft 18 which is coupled to the adjusting ring 7 via a linkage lever 20 provided with a roller 19, and which follows the movement forced on the adjusting ring 7.
  • the rotation of the shaft 18 is used to control further adjusting rings which is attached to further adjusting rings via analog coupling devices 19, 20.
  • FIG. 2 corresponds essentially to that of FIG. 1 with the difference that the transmission lever 11a is no longer pivoted in the support housing 10a, but on the adjusting ring 7a. Furthermore, two expansion rods 9a and 9b are articulated on the transmission lever 11a, both of which have approximately the same coefficient of linear expansion. The expansion rods 9a and 9b are each pivotally articulated at their other end with respect to the support housing 10a. In this embodiment, the position of the adjusting ring 7a is changed in that the two extension rods 9a and 9b change in their axial extent, and thus lead to a change in the position of the transmission lever 11a.
  • the adjusting ring 7a also actuates a pivot lever 21, the shaft 22 of which (in analogy to the shafts 15 of the guide vane 5 via pivot lever 6) is connected to the adjusting ring 7a.
  • a push rod 23 is attached, which is connected to other collars of other rows of guide vanes.
  • FIG. 3 shows the mode of operation of the push rod 23, which is connected on the one hand to an adjusting ring 7b and on the other hand to different adjusting rings 7c, 7d, 7e.
  • the adjusting ring 7b is connected to the adjusting device according to the invention with the difference that no adjusting vanes are directly adjusted by the adjusting ring 7b, but that only one adjusting signal is taken from it.
  • the compressor 24 shown has a flow channel 3a narrowing in the axial direction, with compressor blades 2 and guide blades 5 and 25 being provided alternately.
  • the front guide vanes 5 are adjustable in the flow direction, while the rear guide vanes 25 are rigidly attached to the flow channel wall 4.
  • a plurality of L-shaped adjustment levers 26a, b, c are articulated on the push rod 23.
  • the second lever arms are connected via forks 27 to the adjusting rings 7c, 7d and 7e.
  • This movement of the adjusting rings 7c, d, e in the circumferential direction is converted into a pivoting of the guide vanes 5 via the kinematics already described in the context of FIG. 1.
  • the ratio of the lever arms of the adjustment levers 26a, b, c is individually selected so that an optimal adjustment of the associated guide vanes 5 can be achieved.
  • the adjustment of the adjusting ring 7 and thus the guide vane 5 can be carried out in addition to the thermal scattering via the electronic engine control unit in that the expansion rod 9 is moved forwards or backwards in its axial direction by means of a connected actuating gear 28 (FIG. 5).
  • This relative movement to the support housing 10 is amplified via the transmission lever 11 and passed on to the rotary ring 7 by means of the connecting shaft 14, so that it is displaced in a defined manner in the circumferential direction.
  • This movement is in turn passed on to the radial shafts 15 of the guide vanes 5 via the pivot levers 6, so that the latter are pivoted.
  • a push rod 29 is axially extended on the expansion rod 9 and is guided through the support housing 10 via a bushing 30.
  • the actuating gear 28 itself is fastened to the support housing 10 and is controlled by the drive unit control unit 31.
  • an externally controlled or regulated blade adjustment can be superimposed.
  • a "coarse" adjustment that can be achieved by the thermal adjustment can be finely adjusted, or unsteady adjustments or rapid adjustments can be carried out without delays that may occur in the thermal control circuit.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
EP90107101A 1989-04-21 1990-04-12 Dispositif pour la variation du calage des aubes de stator Expired - Lifetime EP0393531B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3913102A DE3913102C1 (fr) 1989-04-21 1989-04-21
DE3913102 1989-04-21

Publications (2)

Publication Number Publication Date
EP0393531A1 true EP0393531A1 (fr) 1990-10-24
EP0393531B1 EP0393531B1 (fr) 1992-11-04

Family

ID=6379125

Family Applications (1)

Application Number Title Priority Date Filing Date
EP90107101A Expired - Lifetime EP0393531B1 (fr) 1989-04-21 1990-04-12 Dispositif pour la variation du calage des aubes de stator

Country Status (4)

Country Link
US (1) US5035572A (fr)
EP (1) EP0393531B1 (fr)
JP (1) JPH02301601A (fr)
DE (1) DE3913102C1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2688827A1 (fr) * 1992-03-18 1993-09-24 Snecma Systeme de commande d'aubes de stator a calage variable, pour un turboreacteur.

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4102188C2 (de) * 1991-01-25 1994-09-22 Mtu Muenchen Gmbh Leitschaufel-Verstelleinrichtung einer Turbine eines Gasturbinentriebwerks
FR2739137B1 (fr) * 1995-09-27 1997-10-31 Snecma Dispositif de commande d'un etage d'aubes a calage variable
US6240727B1 (en) * 2000-04-27 2001-06-05 The United States Of America As Represented By The Secretary Of The Navy Manufacture of Nitinol rings for thermally responsive control of casing latch
DE10352099B4 (de) 2003-11-08 2017-08-24 MTU Aero Engines AG Vorrichtung zum Verstellen von Leitschaufeln
DE102004004976A1 (de) 2004-01-31 2005-08-18 Mtu Aero Engines Gmbh Vorrichtung zum Verstellen von Leitschaufeln
ATE403798T1 (de) * 2006-01-02 2008-08-15 Siemens Ag Vorrichtung zur abstützung eines einen kreisförmigen schaufelträger beabstandet umgreifenden stellrings
DE102008033560A1 (de) * 2008-07-17 2010-01-21 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinentriebwerk mit verstellbaren Leitschaufeln
US9587632B2 (en) 2012-03-30 2017-03-07 General Electric Company Thermally-controlled component and thermal control process
US9671030B2 (en) 2012-03-30 2017-06-06 General Electric Company Metallic seal assembly, turbine component, and method of regulating airflow in turbo-machinery
US9422825B2 (en) 2012-11-05 2016-08-23 United Technologies Corporation Gas turbine engine synchronization ring
US9546559B2 (en) * 2013-10-08 2017-01-17 General Electric Company Lock link mechanism for turbine vanes
DE102015004648A1 (de) * 2015-04-15 2016-10-20 Man Diesel & Turbo Se Leitschaufelverstellvorrichtung und Strömungsmaschine
US9816390B2 (en) * 2015-07-01 2017-11-14 Hamilton Sundstrand Corporation Electric actuator for engine control
JP6674763B2 (ja) * 2015-11-04 2020-04-01 川崎重工業株式会社 可変静翼操作装置
CN113623271B (zh) * 2020-05-06 2024-07-26 中国航发商用航空发动机有限责任公司 燃气轮机、可调导叶调节机构及其联动环限位装置
DE102021123772A1 (de) 2021-09-14 2023-03-16 MTU Aero Engines AG Verstellanordnung für verstellschaufeln einer strömungsmaschine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2305311A (en) * 1937-07-07 1942-12-15 Jendrassik George Gas turbine plant equipped with regulating apparatus
US2697326A (en) * 1951-04-30 1954-12-21 Ca Nat Research Council Reactor with adjustable stator blades
US2809803A (en) * 1951-04-30 1957-10-15 Ca Nat Research Council Turbine with adjustable stator blades
US3038698A (en) * 1956-08-30 1962-06-12 Schwitzer Corp Mechanism for controlling gaseous flow in turbo-machinery
US3628329A (en) * 1970-02-24 1971-12-21 Gen Electric Gas turbine engine inlet guide vane actuator with automatic reset
US3904309A (en) * 1974-08-12 1975-09-09 Caterpillar Tractor Co Variable angle turbine nozzle actuating mechanism

Family Cites Families (8)

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Publication number Priority date Publication date Assignee Title
CA628826A (en) * 1961-10-10 The Garrett Corporation Temperature responsive variable means for controlling flow in turbomachines
US2929546A (en) * 1955-01-26 1960-03-22 Gen Electric Positioning device
US2932440A (en) * 1955-05-20 1960-04-12 Gen Electric Compressor blade adjustment means
US3377799A (en) * 1966-01-03 1968-04-16 Gen Electric Mechanical integrators and control systems employing same
DE2907748C2 (de) * 1979-02-28 1987-02-12 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Einrichtung zur Minimierung und Konstanthaltung des Schaufelspitzenspiels einer axial durchströmten Hochdruckturbine eines Gasturbinentriebwerks
US4391093A (en) * 1981-06-29 1983-07-05 General Electric Company Temperature-responsive actuator
US4619580A (en) * 1983-09-08 1986-10-28 The Boeing Company Variable camber vane and method therefor
JPS61193396A (ja) * 1985-02-21 1986-08-27 株式会社村田製作所 薄膜ｅｌ素子

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2305311A (en) * 1937-07-07 1942-12-15 Jendrassik George Gas turbine plant equipped with regulating apparatus
US2697326A (en) * 1951-04-30 1954-12-21 Ca Nat Research Council Reactor with adjustable stator blades
US2809803A (en) * 1951-04-30 1957-10-15 Ca Nat Research Council Turbine with adjustable stator blades
US3038698A (en) * 1956-08-30 1962-06-12 Schwitzer Corp Mechanism for controlling gaseous flow in turbo-machinery
US3628329A (en) * 1970-02-24 1971-12-21 Gen Electric Gas turbine engine inlet guide vane actuator with automatic reset
US3904309A (en) * 1974-08-12 1975-09-09 Caterpillar Tractor Co Variable angle turbine nozzle actuating mechanism

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 10, no. 242 (M-509)(2298) 21 August 1986, & JP-A-61 072803 (MITSUBISHI) 14 April 1986, *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2688827A1 (fr) * 1992-03-18 1993-09-24 Snecma Systeme de commande d'aubes de stator a calage variable, pour un turboreacteur.

Also Published As

Publication number Publication date
US5035572A (en) 1991-07-30
EP0393531B1 (fr) 1992-11-04
JPH02301601A (ja) 1990-12-13
DE3913102C1 (fr) 1990-05-31

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