EP2011965A2 - Dispositif et procédé pour serrer des disques de rotor portant des aubes d'un moteur à réaction - Google Patents

Dispositif et procédé pour serrer des disques de rotor portant des aubes d'un moteur à réaction Download PDF

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Publication number
EP2011965A2
EP2011965A2 EP08158102A EP08158102A EP2011965A2 EP 2011965 A2 EP2011965 A2 EP 2011965A2 EP 08158102 A EP08158102 A EP 08158102A EP 08158102 A EP08158102 A EP 08158102A EP 2011965 A2 EP2011965 A2 EP 2011965A2
Authority
EP
European Patent Office
Prior art keywords
tie rod
blisks
clamping
arrangement
rotor
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
EP08158102A
Other languages
German (de)
English (en)
Other versions
EP2011965A3 (fr
EP2011965B1 (fr
Inventor
Sacha Pichel
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2011965A2 publication Critical patent/EP2011965A2/fr
Publication of EP2011965A3 publication Critical patent/EP2011965A3/fr
Application granted granted Critical
Publication of EP2011965B1 publication Critical patent/EP2011965B1/fr
Ceased legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/025—Fixing blade carrying members on shafts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/066—Connecting means for joining rotor-discs or rotor-elements together, e.g. by a central bolt, by clamps

Definitions

  • the invention relates to a device for clamping bladed rotor disks of a jet engine and a use of the device in a jet engine. Furthermore, the invention relates to a method for clamping bladed rotor disks with the device in a jet engine.
  • the turbine and compressor are usually arranged on a shaft.
  • the compressor consists of several rotor discs, each carrying a row of blades and are welded or bolted together.
  • the US 6,267,553 B1 discloses a gas turbine with a high pressure compressor in which there are a plurality of tubular tie rods.
  • the tie rods are guided through openings in the rotor disks, which are arranged radially around the center of the disk.
  • the bracing is done by screws, which are screwed into the internal thread of the tie rods.
  • the US 5,537,814 describes a tie rod for a gas turbine engine that clamps not only the rotor disks of the compressor but also those of the turbine.
  • the tie rod here is a hollow shaft, which is bolted to the blisk in the first stage. Downstream of a radial compressor impeller, a nut is threaded onto a thread of the tie rod to tension the tie rod.
  • An undivided shaft also allows no separate modular design of compressor and turbine.
  • the air passage of a possibly existing vortex rectifier is difficult.
  • the length of the tie rod and various materials and expansion coefficients of the discs complicate the thermal balance between the shaft and rotor and thus maintaining a uniform biasing force.
  • the variable during operation biasing force and the length of the tie rod deteriorate the rigidity of the rotor.
  • the temperature gradient along the disk should be relatively low.
  • the uniform temperature inside the rotor leads to considerable temperature gradients for individual disks.
  • the invention is therefore an object of the invention to provide a device for clamping bladed rotor discs, which is easy to assemble and disassemble.
  • a device for clamping bladed rotor disks of a jet engine which essentially comprises an axial compressor with several bladed rotor disks, at least one turbine section, at least one shaft and at least one tie rod, wherein at least two bladed rotor disks are formed on the compressor inlet side as Blisks, each forming a one-piece embodiment of a rotor disk with circumferentially distributed blades, the Blisks releasably clamped by the tie rod and the other rotor discs separately and independently of the tie rod connected together.
  • the clamping of the blisks with the help of a tie rod allows easy assembly and disassembly both during installation and during maintenance or in case of damage.
  • the blisks can be easily installed or removed without, e.g. multiple glands must be solved.
  • the tie rod is substantially tubular, disposed within central apertures in the blisk-formed rotor discs, and fixedly connected to a shaft which is driven by at least one turbine section.
  • the existing in the blisks anyway central openings can be used well for mounting and dismounting of the tie rod, and there are no additional holes in the discs required.
  • the tie rod is not passed through the rotor discs following in the flow direction on the Blisks, so that the disc diameter of these rotor discs need not be increased.
  • the blisks are by means of the tie rod between at least a first arrangement, which is upstream of the Blisks, and at least one second arrangement, downstream of the Blisks is located and connected to a rotor disk which is adjacent to the Blisks, clamped. In this way it is ensured that the blisks can be clamped independently of the connection between the other rotor disks.
  • the first arrangement comprises a stop arrangement and the second arrangement comprises a clamping arrangement. Due to the clamping arrangement, the blisks can be clamped in a simple manner relative to the stop arrangement.
  • the stop assembly includes upstream of the blisk an extension of a blisk of the first stage adjacent to a stop on the tie rod. This represents a simple embodiment of a stop arrangement.
  • the clamping arrangement comprises at least one clamping element, which serves to transmit power between the tie rod and the rotor disk.
  • the tensioning element is substantially annular and has a flange-shaped, radially outwardly directed attachment portion, an axial tubular center portion and a radially inwardly directed tension portion.
  • the radially outwardly directed attachment portion of the tension member is secured to a portion of the rotor disc which is adjacent to the blisks downstream. As a result, the voltage generated in the clamping element and in the tie rod is transmitted to the rotor disk.
  • the radially outwardly directed attachment portion of the clamping element is located on a radially inner portion attached to the rotor disk, which is adjacent to the Blisks downstream.
  • the attachment portion of the tensioning element is attached to a radially inner portion of the rotor disc, which is adjacent to the Blisks downstream.
  • the power transmission takes place in this case without major deflections.
  • the tie rod has at its downstream end a shoulder whose outer diameter is smaller than the outer diameter of an upstream adjacent portion of the tie rod, and the radially inwardly directed clamping portion of the clamping element enclosing the shoulder radially, wherein the radially inwardly directed clamping portion of the clamping element axially displaceable relative to the shoulder and spaced from an axial boundary of the shoulder in operation and adjacent to the clamping means.
  • This arrangement offers the advantage of a low construction cost and good mounting and dismounting.
  • the tensioning means may in particular be a tie-rod nut, which can be screwed onto an external thread on the shoulder of the tie rod. Due to the tie rod nut, the tension between the blisks is easily adjustable.
  • the first arrangement upstream of the blisk comprises a tensioning arrangement with a tensioning means and the second arrangement downstream of the blisk comprises at least one screw connection between the tensioning bolt and the rotor disk.
  • the upstream end of the tie rod radially adjoins from the inside to a tubular upstream Prolonging the first level blisk.
  • the tensioning means is axially adjacent to the extension and radially to the tensioning ring adjacent to the upstream end of the tie rod, and the tension anchor has a flange at its downstream end which attaches to the rotor disc adjacent the blisk downstream is.
  • the first arrangement serves to generate a voltage with respect to the rotor disk, which is adjacent to the Blisks downstream, and has a very low construction costs.
  • the clamping device is easily accessible from the compressor inlet side.
  • the tie rod has a conical extension in the flow direction, and the flange of the tie rod is attached to a radially outer portion of the rotor disc, which is adjacent to the Blisks downstream. This allows for clamping of the blisks near the blade and good sealing between the blisks. When attached to the radially outer portion of the rotor disc, which is adjacent to the Blisks downstream, occurs a low bending stress of the rotor disc during tensioning of the tie rod.
  • the upstream end of the tie rod is fastened to the tie rod ring with at least one screw connection, which has an external thread, and the tensioning means is a tie nut, which is screwed onto the external thread of the Glasankerrings.
  • the tie-rod nut makes it easy to adjust the tension in the tie rod ring, in the screw connections and in the tie rod.
  • the clamping means simultaneously clamps a radially inner bearing ring of a Switzerlandankerlagers.
  • the clamping means simultaneously clamps a radially inner bearing ring of a Switzerlandankerlagers.
  • At least one tube-type vortex rectifier may be attached to the rotor disc adjacent the blisks downstream.
  • the vortex rectifier flows compressed, heated air in the radial direction from outside to inside and is passed to the turbine for cooling.
  • By placing the vortex rectifier outside the blisks local heating in the disk area of the blisks is avoided. Also, the attachment of the vortex rectifier outside the blisks is easier.
  • the object is achieved by using the above-described device for clamping blisks in a jet engine.
  • the device has a low construction cost and is robust at the same time.
  • the object is achieved by a method for clamping blisks with the device described above, in which the blisks are releasably clamped by means of the tie rod and the other rotor discs are connected separately and independently of the tie rod together.
  • the separate clamping of the blisks allows for easy assembly and disassembly of the blisks.
  • the blisks are clamped by means of the tie rod between an assembly located upstream of the blisk and an assembly located downstream of the blisk and connected to a rotor disc adjacent the blisks downstream.
  • the tie rod is tensioned by the second arrangement located downstream of the blisks.
  • the tie rod can be stretched from the first arrangement located upstream of the blisk.
  • a good accessibility of the arrangement is given.
  • a rotor 1 of a nine-stage axial compressor which has six rotor disks formed as blisks 6, three rotor disks 4, 9 with rotor blades 5, and at least one vortex rectifier 38.
  • the rotor 1 has a device 3 according to the invention for clamping the blisks 6.
  • the first six bladed rotor disks 6 in the flow direction 40 are designed as blisks 6.
  • the blisks 6 are bladed rotor disks in which one disk is integrally formed with the associated blades.
  • On the Blisks 6 follow in the flow direction 40 three bladed Rotor disks 4, 9, the blades 5 are releasably attached.
  • the rotor disk 9 adjoins the last blisk 6 in the flow direction 40.
  • Each blisk 6 has close to the rotor blades 5 at least one axial extension 44, which abuts at least one adjacent blisk 6 respectively.
  • the rotor disk 9 abuts close to the rotor blades 5 with an axial extension 43 to the last in the flow direction 40 Blisk 6.
  • first embodiment of the device 3 comprises a tie rod 12, a stop assembly 27 and a clamping assembly 28 which in Fig. 2 is shown enlarged.
  • the tie rod 12 is tubular and has at its upstream end 21 a radially inwardly recessed shoulder 42 with a stop 16. At its downstream end 14 (FIG. Fig. 2 ), a shoulder 15 is provided, which is set back radially inwardly relative to an axial section 19 of the tie rod 12 and is limited by an axial boundary 17 against the flow direction 40.
  • the shoulder 15 may also have a sprocket.
  • the tie rod 12 is disposed centrally within openings 8 in the blisks 6. It adjoins at its upstream end 21 in the stop assembly 27 to a blisk 6 of the first stage of the compressor. At its downstream end 14 of the tie rod 12 is connected via the clamping assembly 28 with the downstream of the Blisks 6 rotor disk 9.
  • the stop assembly 27 is located at the upstream end 21 of the tie rod 12 and is formed by a stop 16, a shoulder 42 and an extension 7 of the blisk 6 of the first stage of the compressor.
  • the stop 16 forms an axial boundary of the shoulder 42 in the flow direction 40.
  • the extension 7 of the blisk 6 of the first stage of the compressor extends axially against the flow direction 40 to the stop 16. It encloses the shoulder 16 radially, but it is axially displaceable ,
  • enlarged clamping arrangement 28 includes the shoulder 15 of the tie rod 12, a clamping element 33, a tie nut 37, a plurality of screw 29 and adjoins the rotor disc 9, which is adjacent to the Blisks downstream, at.
  • the clamping element 33 comprises a, a flange forming, radial mounting portion 34, a center portion 35 and a clamping portion 36th
  • the center portion 35 of the clamping element 33 is tubular and extends in the mounted state axially and parallel to the tie rod 12.
  • the flange-like mounting portion 34 is directed from the downstream end of the clamping element 33 from radially outward.
  • the clamping portion 36 is directed radially inward from the upstream end of the clamping element 33 and may have a toothed ring.
  • the clamping element 33 is fastened with its fastening section 34 by means of screw connections 29 to an inner section 10 of the rotor disk 9.
  • the clamping portion 36 protrudes in the assembled state of the clamping device 28 parallel to the axial boundary 17 and in the axial direction of this radially inwardly and surrounds the shoulder 15, wherein the clamping portion 36 but against the shoulder 15 is axially displaceable. If sprockets are present on the shoulder 15 and on the tensioning section 36, the toothing of the tensioning section 36 engages in the toothing of the shoulder 15. In the flow direction 40, the tie rod nut 37, which is screwed onto the external thread 18, adjoins the tensioning section 36.
  • the radially outwardly directed fastening section 34 of the clamping element 33 designed as a flange is first fastened by means of a plurality of circumferentially distributed screw connections 29 on the inner section 10 of the rotor disk 9, which adjoins the blisk downstream.
  • the blisks 6 are pushed onto the tie rod 12.
  • the tie rod 12 is then inserted with the shoulder 15 in the annular clamping element 33.
  • the tie nut 37 is screwed onto the external thread 18 of the tie rod 12 and tightened.
  • the tensile force in the clamping element 33 is transmitted from the radially inwardly directed clamping section 36 via the axial center section 35, the radially outwardly directed fastening section 34 and the screw connections 29 to the radially inner section 10 of the rotor disk 9. From there, the force in the rotor disk 9, which is adjacent to the Blisks downstream, in the radial direction outward into the axial extension 43rd the rotor disk 9 forwarded.
  • the tensile force in the tie rod 12 is transmitted along the tie rod 12 on the shoulder 16.
  • the two tensile forces cause compressive forces between the axial extension 43 of the rotor disk 9, the abutting blisks 6 and the abutment 16 of the upstream abutment arrangement 27 via the extensions 44. These compressive forces press the blisks 6 against the extensions 44 of the blisks 6 near the blades 5 axially together and cause the restraint.
  • the compressive forces must be large enough to hold the blisks 6 together. But they must not be too large, so that the stressed components of the device 3, namely the tie rod 12, the external thread 18 on the tie rod 12, the clamping element 33, the screw 29 or the internal thread of the tie nut 37 are not overloaded during operation.
  • FIG. 3 and 4 shows the second embodiment of the device 3 according to the invention, in which the rotor 1 of the compressor is constructed the same as in Fig. 1 ,
  • the second embodiment of the device 3 comprises a tie rod 47, a plurality of screw connections 41 and a clamping arrangement 30, which in Fig. 4 is shown enlarged.
  • the tie rod 47 has a conical enlargement 20 in the flow direction 40. At its upstream end 21 of the tie rod 47 has a radially inwardly directed flange 45. The conical extension points its downstream end a flange 13 which is directed radially outward.
  • the tie rod 47 is arranged centrally within openings 8 in the blisks 6. It adjoins at its upstream end 21 radially from the inside to an axial extension 7 of the blisk 6 of the first stage of the compressor. At its downstream end, the tie rod 47 is connected via a plurality of screw connections 41 distributed over the circumference to the rotor disk 9 adjoining the blisks 6 and adjoining the blisks downstream.
  • the screw connections 41 are distributed in the circumferential direction on a radially outer section 11 of the rotor disk 9, which adjoins the blisks downstream.
  • the flange 13 is fastened to the rotor disk 9 at the end of the conical enlargement 20 of the tie rod 47.
  • the upstream tensioning assembly 30 is in Fig. 4 shown enlarged and includes a Glasankerring 24, a plurality of screw connections 32, a first spacer ring 31, a second spacer ring 39, a Switzerlandankerlager 25 and a Switzerlandankermutter 37th
  • the Buchankerring 24 is annular and has the same outer diameter as the tie rod 47.
  • the Buchankerring 24 has at its adjacent to the tie rod 47 end a radially inwardly directed flange 46.
  • the Buchankerring 24 also has a shoulder 23 whose outer diameter is smaller than the diameter of the upstream end 21 of the tie rod 47.
  • At the upstream end of the Buchankerrings 24 is an external thread 22 whose diameter is smaller than that of the paragraph 23rd
  • the first spacer ring 31 is annular and has substantially the same inner diameter as the axial extension 7 of the blisk 6 of the first stage of the compressor.
  • the second spacer ring 39 is also annular.
  • the tie rod bearing 25 is a ball bearing with a radially inner bearing ring 26th
  • the Buchankerring 24 abuts in the axial direction of the upstream end 21 of the tie rod 47 and forms an axial extension of the tie rod 47 against the flow direction 40.
  • the Buchankerring 24 is secured by means of several screw 32 on the flange 45 of the tie rod 47. In the radial direction, the Glasankerring 24 abuts the first spacer ring 31 from the inside.
  • the extension 7 encloses the tie rod 47 in the radial direction, wherein the extension 7 is displaceable relative to the tie rod 47.
  • the first spacer ring 31 encloses the tie rod 47 in the region of the flange 45 and the Wernerring 24, but with a displacement in the axial direction is given.
  • the first spacer ring 31 adjoins the extension 7 of the blisk 6 of the first stage of the compressor at its downstream end. At its upstream end of the spacer ring surrounds the shoulder 23 of the Werankerrings 24 in the radial direction, but with a displacement in the axial direction is given.
  • the inner bearing ring 26 of the Buchankerlagers 25 is arranged displaceably in the axial direction on the shoulder 23 of the Buchankerrings 24.
  • the inner bearing ring 26 adjoins the first spacer ring 31 downstream and to the second spacer ring 39 upstream.
  • the second spacer ring 39 also encloses the shoulder 23 of the Buchankerrings 24.
  • the second spacer ring 39 protrudes beyond the upstream end of the paragraph 23 out.
  • the flange 13 is first attached to the downstream end of the tie rod 47 on the rotor disk 9, which adjoins the Blisks downstream. This is done by means of the screw 41.
  • the Blisks 6 are pushed onto the tie rod 47.
  • the Switzerlandankerring 24 is then attached by means of the screw 32 on the tie rod 47.
  • the first spacer ring 31, the inner bearing ring 26 and the second spacer ring 39 are pushed over the Ceiankerring 24.
  • the tie rod nut 37 is screwed onto the external thread 22 of the Ceiankerrings 24 and tightened.
  • the compressive forces must be large enough to hold the blisks 6 together. But you must not too big be so that the claimed to train components of the device 3, namely the Glasankerring 24, the external thread 22 on the tie rod 24 or the internal thread of the tie nut 37, the tie rod 47, the screw 32 and the screw 41 are not overloaded during operation.
  • the vortex rectifier 38 is mounted on the downstream side of the rotor disk 9 adjacent to the blisks in both the first and second embodiments so as to be located between the rotor disk 9 and a rotor disk 4 adjacent to this rotor disk 9 ,
  • thermally and mechanically highly resilient materials are used as materials for the components of the device for clamping rotor disks of a jet engine.
  • the materials of the loaded on train components must have a high tensile strength.
  • the tie rod 12, 47 and the rotor disc 9 must also have a high bending stiffness.
  • the pressure-loaded components must accordingly have a high compressive strength. All components of the devices must also have a high fatigue strength.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP08158102A 2007-07-06 2008-06-12 Dispositif et procédé pour serrer des disques de rotor portant des aubes d'un moteur à réaction Ceased EP2011965B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102007031712A DE102007031712A1 (de) 2007-07-06 2007-07-06 Vorrichtung und Verfahren zum Einspannen von beschaufelten Rotorscheiben eines Strahltriebwerkes

Publications (3)

Publication Number Publication Date
EP2011965A2 true EP2011965A2 (fr) 2009-01-07
EP2011965A3 EP2011965A3 (fr) 2011-05-11
EP2011965B1 EP2011965B1 (fr) 2012-08-08

Family

ID=39791582

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08158102A Ceased EP2011965B1 (fr) 2007-07-06 2008-06-12 Dispositif et procédé pour serrer des disques de rotor portant des aubes d'un moteur à réaction

Country Status (3)

Country Link
US (1) US8152471B2 (fr)
EP (1) EP2011965B1 (fr)
DE (1) DE102007031712A1 (fr)

Cited By (3)

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Publication number Priority date Publication date Assignee Title
EP2383433A1 (fr) * 2010-03-10 2011-11-02 United Technologies Corporation Section de compresseur dotée D'UN TIRANT D'ANCRAGE et aubes statoriques montées sur cantilever
US8328512B2 (en) 2009-06-05 2012-12-11 United Technologies Corporation Inner diameter shroud assembly for variable inlet guide vane structure in a gas turbine engine
EP3026212A1 (fr) * 2014-11-17 2016-06-01 General Electric Company Dégagement de face de grille monobloc

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DE102008060571A1 (de) * 2008-12-04 2010-06-10 Mtu Aero Engines Gmbh Montagevorrichtung für ein Rotorsystem einer Axial-Strömungsmaschine
US8459943B2 (en) * 2010-03-10 2013-06-11 United Technologies Corporation Gas turbine engine rotor sections held together by tie shaft, and with blade rim undercut
US8550784B2 (en) * 2011-05-04 2013-10-08 United Technologies Corporation Gas turbine engine rotor construction
US8784062B2 (en) * 2011-10-28 2014-07-22 United Technologies Corporation Asymmetrically slotted rotor for a gas turbine engine
DE102012203047B4 (de) * 2012-02-28 2018-06-21 Rolls-Royce Deutschland Ltd & Co Kg Wellenanordnung in einer Turbomaschine, insbesondere Flugzeugtriebwerk, mit einem Zuganker zur axialen Verspannung einer Stirnverzahnung, die zwei Teile einer Hohlwelle miteinander verbindet, wobei der Zuganker eine hydraulische Dichtung aufweist
GB201222415D0 (en) 2012-12-13 2013-01-23 Rolls Royce Plc Drum seal
EP2826958A1 (fr) * 2013-07-17 2015-01-21 Siemens Aktiengesellschaft Rotor pour une turbomachine thermique
WO2015081037A1 (fr) 2013-11-26 2015-06-04 General Electric Company Ressort de support de boulon de liaison radial
EP3012411A1 (fr) 2014-10-23 2016-04-27 United Technologies Corporation Rotor à aubage intégral ayant un bras axial et une poche
US10125785B2 (en) * 2015-10-16 2018-11-13 Pratt & Whitney Reduced stress rotor interface
GB201611674D0 (en) * 2016-07-05 2016-08-17 Rolls Royce Plc A turbine arrangement
US10927709B2 (en) * 2018-06-05 2021-02-23 Raytheon Technologies Corporation Turbine bearing stack load bypass nut
US10954861B2 (en) * 2019-03-14 2021-03-23 Raytheon Technologies Corporation Seal for a gas turbine engine
CN114876580B (zh) * 2022-07-12 2022-09-27 陕西联信材料科技有限公司 一种飞机制造用航空发动机涡轮叶片组件及其制备方法

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US5537814A (en) 1994-09-28 1996-07-23 General Electric Company High pressure gas generator rotor tie rod system for gas turbine engine
US6267553B1 (en) 1999-06-01 2001-07-31 Joseph C. Burge Gas turbine compressor spool with structural and thermal upgrades

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8328512B2 (en) 2009-06-05 2012-12-11 United Technologies Corporation Inner diameter shroud assembly for variable inlet guide vane structure in a gas turbine engine
US8951010B2 (en) 2009-06-05 2015-02-10 United Technologies Corporation Inner diameter shroud assembly for variable inlet guide vane structure in a gas turbine engine
EP2383433A1 (fr) * 2010-03-10 2011-11-02 United Technologies Corporation Section de compresseur dotée D'UN TIRANT D'ANCRAGE et aubes statoriques montées sur cantilever
EP3026212A1 (fr) * 2014-11-17 2016-06-01 General Electric Company Dégagement de face de grille monobloc
US10731484B2 (en) 2014-11-17 2020-08-04 General Electric Company BLISK rim face undercut

Also Published As

Publication number Publication date
EP2011965A3 (fr) 2011-05-11
DE102007031712A1 (de) 2009-01-08
US8152471B2 (en) 2012-04-10
EP2011965B1 (fr) 2012-08-08
US20090016886A1 (en) 2009-01-15

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