EP2573328A1 - Anneau de stator pour turbomachine et procédé de fonctionnement de l'anneau de stator - Google Patents

Anneau de stator pour turbomachine et procédé de fonctionnement de l'anneau de stator Download PDF

Info

Publication number
EP2573328A1
EP2573328A1 EP11181917A EP11181917A EP2573328A1 EP 2573328 A1 EP2573328 A1 EP 2573328A1 EP 11181917 A EP11181917 A EP 11181917A EP 11181917 A EP11181917 A EP 11181917A EP 2573328 A1 EP2573328 A1 EP 2573328A1
Authority
EP
European Patent Office
Prior art keywords
stator ring
vane
fastener
turbomachine
adjusting means
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP11181917A
Other languages
German (de)
English (en)
Inventor
Janos Szijarto
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP11181917A priority Critical patent/EP2573328A1/fr
Priority to PCT/EP2012/068035 priority patent/WO2013041451A1/fr
Publication of EP2573328A1 publication Critical patent/EP2573328A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F01D9/02—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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise

Definitions

  • the present invention relates to a stator ring for a turbomachine
  • a turbomachine is a device that is used for generating thrust by means of increasing the velocity of air flowing through it. It is used in different fields, for example, power generation, gas turbines, jet engines, et cetera.
  • the mechanism of operation of the turbomachine primarily spans four sequential stages, viz., intake, compression, combustion, and exhaust. Air flows from outside through an air inlet into the turbomachine during the intake stage, during which the air is streamlined and directed towards a compressor. In the compression stage, the compressor compresses the air, which packs the air in a tight manner, thereby increasing its pressure. This results in an increased quantity of oxygen available per unit volume of air used during combustion.
  • the combustion stage involves mixing the compressed air with fuel and igniting the mixture in one or more combustors at a constant pressure.
  • the ignition of the mixture leads to an expansion of the air and an increase in temperature.
  • the expanded air is directed towards a nozzle, which is construed to be an outlet of the turbomachine.
  • An outflow of the expanded air at high pressure through the nozzle results in the generation of thrust in a direction opposite to the direction of outflow.
  • a turbine with a rotor comprising blades and a stator ring comprising vanes is located between the one or more combustors and the nozzle.
  • the turbine is in turn coupled to an electric generator.
  • the hot and expanded air flowing out of the combustor acts on the blades of the turbine, which in turn rotates the turbine and consequently the generator, thereby generating electric power. A major portion of this power is fed back to the compressor for running the compressor.
  • the stator ring comprising the vanes is arranged such that the vanes direct the flow of air from the combustor onto the blades of the turbine.
  • the stator ring can be spatially arranged in a circumferential manner around the rotor.
  • the aforesaid problem can be solved by influencing the vibration frequency of the vane.
  • the vibration frequency of a single vane is adjusted by modifying the design of the vane. This entails changing the geometry of the vane, which is an expensive solution. It involves casting and tooling changes, which is not only inflexible but also non-retrofittable.
  • stator ring for a turbomachine according to claim 1 and a method for operation of the stator ring according to claim 13.
  • a stator ring for a turbomachine comprises a vane coupled to the stator ring by a coupling means and an adjusting means in interaction with the vane.
  • the adjusting means is capable of influencing vibrations of the vane during operation of the turbomachine. This influence of the adjusting means on the vane, for example, results in a dampening of the vibrations and the vibration frequency respectively. When the vibrations are dampened, the mechanical damage incurred by both the stator ring and the vane is minimized, thereby increasing the lives of both the stator ring and the turbomachine.
  • the coupling means is made of a first coupling means provided on the stator and a second coupling means provided on the vane.
  • the coupling between the first coupling means and the second coupling means secures the vane onto the stator ring, advantageously rendering a stable coupling.
  • the activation of the adjusting means tightens the first coupling means and the second coupling means.
  • the tightening of the first and second coupling means stiffens the coupling, thereby fixing the vane tightly onto to the stator ring. Furthermore, this renders a provision of influencing the vibration frequency by tightening the adjusting means.
  • the activation of the adjusting means changes the mechanical tension of the vane.
  • the activation increases the mechanical tension on the vane when the adjusting means is further tightened, thereby influencing the vibration frequency of the vane to a greater extent.
  • the adjusting means is arranged in a manner that establishes a mechanical contact between the stator ring and the vane.
  • the operation of the turbomachine results in vibration of the vane at certain frequencies.
  • the manner of arrangement has an influencing effect on these vibrations, such that the adjusting means dampens the vibrations of the vane. This maintains smooth operation of the turbomachine and causes fewer disruptions.
  • the adjusting means is in the form of a hole on the stator ring along with a fastener provided through the hole.
  • the fastener interacts with the vane and the activation of the fastener displaces the fastener by changing its position relative to the stator ring.
  • the frequency of vibration of the vane is capable of being influenced and reduced from outside by this simple mechanism.
  • the fastener is controllable from the outside, thereby rendering the capability to dampen the vibrations. Furthermore, this is a retrofittable solution and obviates the problem of redesigning and re-moulding the vane to dampen certain vibration frequencies.
  • the fastener is either a bolt or a rivet or a screw.
  • These fasteners are based on simple operating mechanisms and are easy to fix and activate through the hole provided on the stator ring to interact with the vane. Furthermore, the movement and operation of the fastener is controllable from the outside of the stator ring, thereby increasing the convenience of operation of the stator ring.
  • the adjusting means has an actuator for adjusting the position of the fastener.
  • the actuator increases the convenience of operation as the fastener is capable of being operated from a distance.
  • the fastener driven by an actuator is controllable by an electric source, which increases the accuracy and flexibility of its operation.
  • the coupling means is in the form of flanges provided on the stator ring and the vane.
  • a flange on the stator ring and a flange on the vane are coupled that secures the vane onto the stator ring.
  • a flange is one of the simplest and efficient means to couple two dissimilar mechanical components, for example, the stator ring and the vane, in a secured manner.
  • a turbomachine has the stator described according to any of the aforementioned embodiments.
  • the vibrations of the vane of the stator in the turbomachine is capable of being dampened by adjusting the adjusting means.
  • the turbomachine comprises a combustor, and the combustor has a vibration frequency. A resonance of the vibration frequencies of the combustor and the vane is obviated by the stator ring, in which the vibration frequency of the vane is capable of being influenced.
  • the turbomachine comprise either a steam turbine or a gas turbine or a turbofan.
  • the stator ring in a method of operation of a stator ring of a turbomachine, has a vane coupled to the stator ring.
  • An adjusting means interacting with the vane is actuated to influence the vibration of the vane.
  • the influence of the adjusting means on the vane results in a dampening of the vibrations and the vibration frequency respectively.
  • the vibrations are dampened, the mechanical damage incurred by both the stator ring and the vane is minimized, thereby increasing the lives of both the stator ring and the vane.
  • a hole is provided on the stator ring, and a fastener is activated through the hole to interact with the vane.
  • the position of the fastener with respect to the stator ring is varied by tightening the fastener. This influences the vibration frequency of the vane, as the fastening results in stiffening of the coupling between the stator and the vane, thereby damping the vibration frequency of the vane. This also reduces rattling of the vane, if the coupling is loose. Further tightening of the fastener results in an increase in the mechanical tension of the vane and further dampens the vibration frequency.
  • the fastener is adjusted in a manner that annuls the vibration frequency of the vane. This has the advantage of increasing the life of the stator ring and a turbomachine comprising the stator ring, as vibrations are annulled resulting in a smooth operation.
  • FIG 1 depicts a turbomachine 10 with an external casing 20 for generating thrust by means of increasing the velocity of air flowing through it.
  • the turbomachine 10 comprises various sections, viz., an intake section 21, a compression section 22, a combustion section 23, a turbine section 24, and an exhaust section 25, which respectively correspond with various operational stages in a sequential manner.
  • the intake section 21 comprises an air inlet 30, which is interfaced with a compressor 40 of the compression section 22.
  • the compressor 40 is interfaced with a combustor 50, a major entity of the combustion section 23.
  • the combustor 50 is connected to a fuel tank 55 through a pipe 57, which provides fuel for mixing it with the air during combustion.
  • the turbine section 24 is subsequent to the combustor 50 and comprises a turbine 60, which is in turn connected using a turbine shaft 65 to a generator 70.
  • a nozzle 80 subsequent to the turbine 60 serves as an outlet for the air, and marks the final section, i.e., the exhaust section 25.
  • the turbomachine 10 takes in air 90 through the air inlet 30, processes it, and exhausts it from the nozzle 80. During this process, the air 90 is acted upon by various factors related to the different parts of the turbomachine 10. The process is cyclical, and the air 90 being acted upon is the same throughout a cycle. However there is a change in the properties exhibited by the air 90 at various operational sections 21-25 of the turbo machine 10. For example, its pressure, volume, temperature and velocity, are different at the various aforesaid sections, thereby possessing different capabilities at various operational stages.
  • Air 90 at the inlet 30 of the turbomachine 10 is at atmospheric pressure and is directed towards the compressor 40.
  • the air 100 at the inlet of the compressor 40 is streamlined, and is still at atmospheric pressure.
  • the compressor 40 acts upon the air 100 by way of compressing it and subsequently feeding it to the combustor 50.
  • the compressed air 110 is at a higher pressure and occupies lesser volume compared to the air 100 at the inlet of the compressor 40. It also contains more oxygen per unit volume.
  • the fuel in the fuel tank 55 is injected into the combustor 50 through a fuel pipe 57 and mixed with the compressed air 110 inside the combustor 50.
  • the fuel and air 110 mixture is then ignited.
  • the process of combustion takes place at constant pressure, thereby leading to a volumetric expansion of the compressed air 110.
  • Air 120 at the outlet of the combustor 50 possesses higher volume and higher temperature compared to the air 110 at the inlet of the combustor 50.
  • the air 120 acts on the turbine 60, which is in turn connected to the generator 70 using the turbine shaft 65, and rotates the generator 70 and produces power.
  • air 130 after its action on the turbine 60 expands through the nozzle 80 and exhausts the turbomachine 10.
  • Air 140 at the exit of the turbo machine 10 returns to the atmosphere, but possesses higher velocity, temperature and pressure, thereby creating a thrust in a direction opposite to the direction of the air 90.
  • FIG 2 depicts a front view of the turbine of the turbomachine 10 in accordance with an embodiment of the invention. It has a stator in the form of a stator ring 150 comprising a plurality of vanes 155, and a rotor 160 comprising a plurality of blades 165.
  • the rotor 160 comprising the plurality of blades 165 is mounted on the turbine shaft 65.
  • the rotor 160 rotates under the influence of the air 120 coming from the combustor 50.
  • the stator ring 150 comprising the plurality of vanes 155 is a stationary body, and the plurality of vanes 155 act as a means to guide the air 120 entering the turbine 60.
  • the air 120 is guided by the plurality of vanes 155 and it impinges on the plurality of blades 165 of the rotor 160 in a direction axial to the rotor 160.
  • the plurality of blades 165 is arranged in a manner to convert the axial impingement of the air 120 into a rotary motion, thereby rotating the rotor 160, causing the generator 70 to generate power.
  • the flow of the air 120 on the plurality of vanes 155 during the operation of the turbomachine 10 and the structural geometry of the plurality of the vanes 155 result in vibrations of the vanes 155. These vibrations correspond to different frequencies.
  • a plurality of adjusting means 170, which interact with the plurality of vanes 155, are provided on the stator ring 150 to adjust the vibration frequency of the plurality of the vanes 155.
  • the frequency adjustment of the vanes 155 may include either stopping a frequency completely by annulling the frequency or damping the vibrations by reducing the amplitude of the vibrations.
  • the frequency adjustment may also include the flexibility to discretely choose certain frequencies that is to be stopped or damped by means of adjusting the adjusting means 170.
  • the structure and the operating mechanism of the adjusting means 170 for adjusting the vibration frequency of the plurality of the vanes 155 are explained with reference to FIG 3 .
  • FIG 3 The external surface of the stator ring 150 referred to in FIG 2 having a plurality of holes 180 at designated locations corresponding to the locations of the vanes 155 is depicted in FIG 3 .
  • a designated location is defined as that location on the stator ring 150 from which the adjusting means 170 is capable of influencing the vibration frequency of a vane 155.
  • the designated location depicted in FIG 3 and the role of the plurality of adjusting means 170 in adjusting the vibration frequency of the plurality of vanes 155 is to be read and construed with reference to FIG 4 .
  • FIG 4 depicts a technical drawing of a cross-sectional view of the stator ring 150 referred to in FIG 3 , along the section III ⁇ III.
  • a flange is an extended portion and is beneficial in attaching either two similar or dissimilar mechanical structures.
  • a first coupling means is provided in the form of a first flange 190 on the internal periphery of the stator ring 150, and a second coupling means is provided in the form of a second flange 200 on a section of the vane 155.
  • the first flange 190 and the second flange 200 interact with one another by coupling with one another. This means of physical contact facilitates securing the vane 155 onto the stator ring 150.
  • a loose -fit between the first flange 190 and the second flange 200 results in vibrations of the vane 155 during the operation of the turbomachine 10.
  • the plurality of holes 180 on designated locations of the stator ring 150 forms a part of the adjusting means 170.
  • the adjusting means 170 further comprises corresponding fasteners 210 inserted through the holes 180 and they interact with the first flange 190 and the second flange 200.
  • fasteners 210 are bolts that are inserted through the corresponding holes 180.
  • a bolt 210 comprises a head 220, a body 230 and a thread 240.
  • the hole 180 is provided with a thread
  • the body 230 of the bolts 210 is provided with a complementary thread 240 such that the bolt 210 is capable of being fastened into the hole 180 to interact with the vane 155.
  • the radius of the hole 180 and the radius of the body 230 of the bolt 210 are substantially similar, such that the thread of the hole 180 and the complementary thread 240 of the bolt 210 are capable of being fastened in a facile and tight manner.
  • the bolt 210 either tightens or loosens the contact that couples the first flange 190 with the second flange 200.
  • the tightening or loosening of the bolt 210 alters the position of the bolt 210, as it changes the pitch of the thread 240 of the bolt 210.
  • the influence of the fastener 210, that is, the adjusting means 170, on the vibration of the vane 155 depends on the position of the fastener 210.
  • the fastener is provided in the form of a bolt 210.
  • the bolt 210 is activated, by means of tightening it, first the position of the vane 155 relative to the stator ring 150 is influenced, resulting in a tight fit of the vane 155.
  • This increases the stiffness of the coupling between the first coupling means 190 and the second coupling means 200.
  • the mechanical property of the vane 155 changes when the bolt 210 is further tightened.
  • property change can be a change in the mechanical tension or the stiffness of the vane 155.
  • the resulting effects that is, the tight-fit that increases the stiffness between the first coupling 190 and the second coupling 200, and the change of the mechanical property of the vane 155, result in a change of vibration frequency of the vane 155.
  • the tightening of the vane 155 dampens the vibration frequency of the vane 155, thereby obviating the vibrations.
  • the vibrations finally can be completely stopped.
  • the fasteners 210 of the adjusting means 170 can include screws, clamps, rivets, et cetera, which can achieve the aforementioned object.
  • the fasteners can be interfaced with actuators, for example, piezoelectric actuators for tightening or loosening the contact accordingly, thereby being able to adjust the position of the fastener.
  • the adjusting means 170 is a means with a movable component, for e.g., a bolt 210, where the relative position of the bolt with respect to the stator ring 150 is modifiable, thereby generating a force on a vane 155 of the stator ring 150.
  • This force results in a displacement of the vane 155 and in tightening of the coupling means, e.g. flanges 190, 200, which couple the vane 155 to the stator ring 150. Further tightening of the fastener 210 increases the mechanical tension of the vane 155.
  • the actuator is interfaced with the adjusting means 170 for activating the adjusting means 170.
  • the actuator drives the adjusting means 170 in a manner that it displaces the position of the adjusting means 170, for example, tightening or loosening the adjusting means 170.
  • a piezoelectric actuator driving an adjusting means 170 in the form of a bolt 210 activated through the hole 180, the actuator drives the bolt 210 which can either tighten or loosen the coupling between the stator ring 150 and the vane 155. The activation, and the subsequent tightening or loosening of the coupling influences the frequency of vibration of the vane 155.
  • FIG 5 depicts a flowchart of a method for operation of the stator ring 150. This is by adjusting the vibration frequency of a vane 155 attached to a stator ring 150.
  • the stator ring 150 is provided with a hole 180 on its external surface at a designated location and in step 250 the adjusting means 170 is actuated to influence the vibrations of the vane 155.
  • a fastener 210 is fastened though the hole 180 such that the fastener 210 interacts with the vane 155.
  • step 260 the position of the fastener is adjusted such that the fastener is tightened or loosened such that the coupling means of attachment between the stator ring 150 and the vane 155 is adjusted.
  • This adjustment first increases or decreases the mechanical stiffness of the vane 155 and adjusts the vibration frequency of the vane 155.
  • the fastener is adjustable in a manner such that if the fastener is tightened adequately, such that the stiffness of the vane 155 is maximized. Further tightening of the fastener 210 results in by increasing the mechanical tension of the vane 155, for example leading to a change of shape of the vane 155, and influences the vibration frequency further. This can also lead to a near total reduction of the vibration frequency of the vane 155.
  • a turbomachine 10 of FIG 1 which can either be a steam turbine or a gas turbine or a turbofan, comprises the aforementioned stator ring 150.
  • the vibration frequency of the vane 155 of the stator ring 150 in such a turbomachine 10 is adjustable by means of the adjustable means 170.
  • the adjusting means 170 adjusts the vibration frequency of the vane 155 such that the vibration frequency can be dampened even leading to annulment.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP11181917A 2011-09-20 2011-09-20 Anneau de stator pour turbomachine et procédé de fonctionnement de l'anneau de stator Withdrawn EP2573328A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP11181917A EP2573328A1 (fr) 2011-09-20 2011-09-20 Anneau de stator pour turbomachine et procédé de fonctionnement de l'anneau de stator
PCT/EP2012/068035 WO2013041451A1 (fr) 2011-09-20 2012-09-14 Couronne de stator pour une turbomachine et procédé pour l'actionnement de la couronne de stator

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11181917A EP2573328A1 (fr) 2011-09-20 2011-09-20 Anneau de stator pour turbomachine et procédé de fonctionnement de l'anneau de stator

Publications (1)

Publication Number Publication Date
EP2573328A1 true EP2573328A1 (fr) 2013-03-27

Family

ID=46880705

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11181917A Withdrawn EP2573328A1 (fr) 2011-09-20 2011-09-20 Anneau de stator pour turbomachine et procédé de fonctionnement de l'anneau de stator

Country Status (2)

Country Link
EP (1) EP2573328A1 (fr)
WO (1) WO2013041451A1 (fr)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2165529A1 (de) * 1971-12-30 1973-07-05 Kloeckner Humboldt Deutz Ag Einrichtung zum zentrieren und fixieren eines koerpers
EP1083300A2 (fr) * 1999-09-07 2001-03-14 General Electric Company Carter de soufflante avec structure de rétention à double paroi
US20030185683A1 (en) * 2002-04-02 2003-10-02 Christian Seydel Stator vane span attachment for a gas turbine
DE102004006706A1 (de) * 2004-02-11 2005-08-25 Mtu Aero Engines Gmbh Dämpfungsanordnung für Leifschaufeln
EP2072760A1 (fr) * 2007-12-21 2009-06-24 Techspace aero Dispositif de fixation d'aubes a une virole d'étage de stator d'une turbomachine et procède de fixation associe
FR2942638A1 (fr) * 2009-02-27 2010-09-03 Snecma Secteur angulaire de redresseur pour compresseur de turbomachine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2165529A1 (de) * 1971-12-30 1973-07-05 Kloeckner Humboldt Deutz Ag Einrichtung zum zentrieren und fixieren eines koerpers
EP1083300A2 (fr) * 1999-09-07 2001-03-14 General Electric Company Carter de soufflante avec structure de rétention à double paroi
US20030185683A1 (en) * 2002-04-02 2003-10-02 Christian Seydel Stator vane span attachment for a gas turbine
DE102004006706A1 (de) * 2004-02-11 2005-08-25 Mtu Aero Engines Gmbh Dämpfungsanordnung für Leifschaufeln
EP2072760A1 (fr) * 2007-12-21 2009-06-24 Techspace aero Dispositif de fixation d'aubes a une virole d'étage de stator d'une turbomachine et procède de fixation associe
FR2942638A1 (fr) * 2009-02-27 2010-09-03 Snecma Secteur angulaire de redresseur pour compresseur de turbomachine

Also Published As

Publication number Publication date
WO2013041451A1 (fr) 2013-03-28

Similar Documents

Publication Publication Date Title
US8943840B2 (en) Mounting assembly
JP6438926B2 (ja) ガスタービンエンジンのためのねじり制振
WO2010097980A1 (fr) Turbocompresseur d'échappement de type à capacité variable
EP3085967B1 (fr) Mécanisme à aube de stator à calage variable
JP6200418B2 (ja) ラジアルタービン、特に補助動力源タービン用の可変ピッチノズル
US20220025823A1 (en) Hybrid electric fan with stall free low pressure compressor
EP3318716B1 (fr) Installation ou dépose d'aube de turbine sur l'emplanture d'aube de turbine
US20080000216A1 (en) Turbofan engine
US9133723B2 (en) Shield system for gas turbine engine
FR2968047A1 (fr) Compresseur et son procede d'utilisation
JP6196442B2 (ja) タービンシュラウド向けの成形ハニカムシール
JP5123400B2 (ja) ガイド・デバイス
WO2013192378A1 (fr) Système d'amortisseur d'extrémité de liaison sphérique à mise en prise quasi-constante
EP2573328A1 (fr) Anneau de stator pour turbomachine et procédé de fonctionnement de l'anneau de stator
JP5342594B2 (ja) ターボ過給機
Pesiridis et al. Active control turbocharger for automotive application: An experimental evaluation
JP2010275973A (ja) 回転機械
US11428120B1 (en) Damping bracket for a gas turbine engine
EP2877727A1 (fr) Support de roulement allongé pour actionneur d'aubes à incidence variable
KR100788915B1 (ko) 슈퍼차저의 동력전달 설치구조
EP4130437A1 (fr) Support de conduit pour moteur de turbine à gaz
US20240052778A1 (en) Variable bleed valves with struts for aerodynamic stability
CN116624433A (zh) 减少翼型件的偏转的方法和设备
EP4281650A1 (fr) Appareil pour le retrait ou l'installation d'une aube de turbine
RU2277187C1 (ru) Осевой компрессор

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

AX Request for extension of the european patent

Extension state: BA ME

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20130928