EP2514923A1 - Dispositif de diaphragme, corps de base de rotor à aubage intégral, procédé et turbomachine - Google Patents

Dispositif de diaphragme, corps de base de rotor à aubage intégral, procédé et turbomachine Download PDF

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Publication number
EP2514923A1
EP2514923A1 EP11162771A EP11162771A EP2514923A1 EP 2514923 A1 EP2514923 A1 EP 2514923A1 EP 11162771 A EP11162771 A EP 11162771A EP 11162771 A EP11162771 A EP 11162771A EP 2514923 A1 EP2514923 A1 EP 2514923A1
Authority
EP
European Patent Office
Prior art keywords
bladed rotor
diaphragm
diaphragm element
integrally bladed
radially
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Withdrawn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
EP11162771A
Other languages
German (de)
English (en)
Inventor
Frank Stiehler
Manuel Hein
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 Aero Engines 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 Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Priority to EP11162771A priority Critical patent/EP2514923A1/fr
Publication of EP2514923A1 publication Critical patent/EP2514923A1/fr
Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means

Definitions

  • the invention relates to a diaphragm device for an integrally bladed rotor main body according to the preamble of patent claim 1, an integrally bladed rotor main body with such a diaphragm device, a method for assembling such integrally bladed rotor body and a turbomachine.
  • Integrally bladed rotor body of a rotor for turbomachinery, such as aircraft engines, with a variety of bonded to a disc or annular body cohesively and forming a row of blades blades have for manufacturing reasons regularly between blade roots or blade shafts adjacent blades a channel-like passage through which axial direction cooling air can flow from the high pressure side to the low pressure side.
  • a cooling air flow through the channels is in the DE 10 2009 007 468 A1 and in the DE 10 2009 011 965 A1 proposed to close the channels on the outlet side, ie the low pressure side, by a diaphragm device.
  • the diaphragm device comprises a sheet-like ring which surrounds the base body and, for example, as in the DE 10 2009 007 468 A1 shown between a radially inner hook-shaped holder and a radially outer hook-shaped holder is arranged.
  • the ring causes a reliable sealing of the channels or a reliable reduction of the channel cross sections, but this is a very precise production necessary to prevent, for example, a flow around the ring in the region of the brackets.
  • An alternative also in the DE 10 2009 007 468 A1 Shutter device shown has a plurality of arranged in the channels and extending beyond the channels also tubular diaphragm elements whose lumen can be reduced or closed. The securing of the diaphragm elements takes place at the ends in each case by means of a flanged tubular collar.
  • a disadvantage of this alternative aperture device is the high assembly and disassembly effort.
  • the object of the invention is to provide a diaphragm device for an integrally bladed rotor main body of a turbomachine, which eliminates the aforementioned disadvantages and also has a good integrability on the component. Furthermore, it is an object of the invention to provide an integrally bladed rotor main body for a turbomachine with an optimized diaphragm device, a method for assembling such an integrally bladed rotor main body and a turbomachine.
  • a diaphragm device for an integrally bladed rotor main body of a turbomachine for adjusting a cooling air flow from a high pressure side to a low pressure side through channels formed between adjacent blades has a ring-like diaphragm element for at least partially covering the channels.
  • the diaphragm element has two attachment diameters for forming a radially inner, axially extending sealing region and for forming a radially outer, radially extending sealing region.
  • the diaphragm device according to the invention is characterized by a good integrability on the rotor base body and can have optimum material properties. Furthermore, it is very robust due to the lack of moving components and is easy to assemble and disassemble.
  • the diaphragm element has an L-shaped cross section with an axial profile section with an outer peripheral contact surface for forming the radially inner sealing region and with a radial profile section with a radial contact surface for forming the radially outer sealing region.
  • the diaphragm element is held in a self-locking manner on a corresponding body portion of the rotor base body in operation in the radial direction during operation due to the centrifugal force.
  • At least one securing element may be provided for securing the diaphragm element.
  • corresponding receptacles in the panel element are preferably formed in a body section outside the sealing areas.
  • An integrally bladed rotor main body according to the present invention for a turbomachine having a plurality of blades coupled to a disk or annular body has an aperture having an aperture member for adjusting a flow of cooling air from a high pressure side to a low pressure side through passages formed between adjacent blades, the diaphragm member forms a radially inner axially extending sealing region and a radially outer radially extending sealing region.
  • Such integrally bladed rotor body is characterized by a very good structural integrity, since the aperture is stored safe and close to the axis of rotation. In addition, it has a good delimitation and guidance of the cooling air flows and hot gas flows or of the respective cooling air flow and hot gas flow.
  • the diaphragm element for forming the radially inner sealing region is mounted with its axial profile section on a base-body-side support ring and is medium or to form the radially outer sealing region with its radial profile section immediately in contact with a blade-side body portion.
  • the diaphragm element is also with its radial profile section against the paddle-side body portion with appropriate design in centrifugal loading.
  • the diaphragm element is secured with its axial profile section by a circlip inserted into an inner circumferential groove of the axial profile section and into an outer peripheral groove of a base body section on the support ring.
  • a positive connection can be easily mounted and is executable in all possible degrees of freedom. In this case, a reaction to the vibration behavior of the blades is prevented by the rotation axis near and moving blade distant circlip.
  • the panel member is pressed with its axial profile section by a clamping ring, which is positively connected to the axial profile section in operative engagement and is guided in the radial direction on a base body portion, against the support ring.
  • the assembly of this embodiment is relatively simple, since the clamping ring in no groove, notch and drgl. Must be inserted, but by the blade side positive engagement and by the radial guide on the body portion automatically in the axial direction and by its outward bias in the radial direction Position secured so that the clamping ring itself does not need to be secured against rotation despite its groove-free arrangement.
  • the diaphragm element is connected with its axial profile section by means of adhesion to the support ring.
  • the frictional connection can be made for example by a press fit and allows a backup of the diaphragm element both in the circumferential and in the axial direction of the rotor body.
  • the adhesion allows in principle a bearing of the diaphragm element without the provision of component jumps forming component contours such as grooves, notches and drgl. For receiving corresponding fuse elements.
  • the frictional connection is weight neutral.
  • the diaphragm element in the third embodiment can additionally be provided to secure the free body portion locking pins which are guided through holes of the diaphragm element and fixed in holes of the blades arranged in sections.
  • the tight fit of the locking pins in the rotor-side bores prevents wear in the operating-blade-side bore area despite blade vibrations under all operating conditions.
  • the locking pins can be guided tolerance tolerances in the holes of the diaphragm element and by means of a holding element with the diaphragm element in operative connection.
  • the vibration behavior of the rotor blades if no direct contact is formed between the diaphragm element and the blade, that is to say if the diaphragm element is in direct contact exclusively with the base body.
  • This blade-side indirect or indirect contact can be done for example by a sealing element in the region of the second sealing area.
  • the sealing element serves as a damping element, so that the moving blades and the diaphragm element mutually dampen and soothe vibrations.
  • the diaphragm element is positioned on the rotor blades and subsequently fixed in position by means of a securing element.
  • the securing element can be positioned both in front of the diaphragm element on the rotor base body or after the diaphragm element.
  • a clamping ring is first inserted in a rotor body-side circumferential chamber on the rotor body, then inserted the diaphragm element in the peripheral chamber and then positioned by a relaxation of the clamping ring, the diaphragm element on the rotor body.
  • first locking pins in run used shovel holes and then pushed the diaphragm element on the locking pins and stored under adhesion to the rotor body.
  • a turbomachine according to the invention has at least one integrally bladed rotor body according to the invention and is distinguished by a high delimitation of its hot gas flow or its hot gas flows from its cooling air flow or its cooling air flows, by a smooth running behavior and by a high ease of maintenance with respect to its blade side axial diaphragm device.
  • FIG. 1 shows a portion of an integrally bladed rotor body 1 for a turbomachine such as an aircraft engine in the flow direction of a hot gas stream viewed in a perspective view obliquely from behind.
  • the rotor base body 1 has a multiplicity of adjacent rotor blades 2 forming a blade row, which are connected to a turbine-side ring-shaped or disk-shaped base body 4.
  • the blades each have a blade root 6, a blade neck 8, an airfoil 10 (see FIG. FIG. 2 ) and a platform 12 arranged between the blade neck 8 and the airfoil 10, with a front high pressure side projection 14 and a rear low pressure side projection 16 viewed in the flow direction.
  • the blade root 6 is formed either as an integral part of the blade 2 or as a separately formed and subsequently joined to the blade 2 component. It is connected to its radially inner peripheral surface cohesively, for example by means of a Reibsch spavons to a base of the base body 4 and has two concave side walls 18, 20, which merge into a base body side extending over the base circumferential wall 22.
  • the blade neck 8 is formed widened viewed in relation to the blade root 6 in the circumferential direction. He has two laterally opposite to each other formed recesses 24 which are surrounded by a respective side surface 26, 28.
  • the side surfaces 26, 28 respectively extend over the projections 14, 16 and are provided in a region remote from the platform and near the channel, each having a downgrading 30 extending in the axial direction.
  • the side surfaces 26, 28 each having a circumferentially extending downgrading 32 for establishing a fluid connection between a cavity 34 formed by the respective opposite recesses 24 (s. FIG. 2 ) and a low pressure side of the blades 2 are provided.
  • the airfoil 10 extends approximately centrally from the platform 12 and is conventional in nature, so that a single explanation is omitted. Basically, it can be provided with an internal cooling system.
  • the platform 12 is formed by the blade neck 8 and forms with platforms 12 adjacent blades 2 a radially outer hot gas flow side annulus 38 and a radially inner cooling air flow side cooling chamber 40 from.
  • High pressure side extends from the front projection 14 in the direction of the base body 4, a plate member 41 for the inlet-side guidance of a cooling air flow.
  • adjacent flow blades 2 each have a lateral contact portion 36.
  • the adjacent blades 2 touch with their opposite side surfaces 26, 28 and thus form the annular space 38 and the cooling chamber 40 from.
  • the opposite side walls 28, 20 of the blades 2 define in the circumferential direction in each case a channel 42, which is in radial fluid communication with the gap 34 formed by the opposing recesses 24 via a gap formed by the downgrades 30.
  • the channels 42 are as clearly in FIG. 1 can be seen obliquely to the rotational axis employed and each have a high-pressure side radially inner inlet and a low-pressure side radially outer outlet.
  • the respective opposite extending in the circumferential direction in the Sectional view invisible gradations 32 of the blades 2 each form a communicating with the cooling chamber 40 in the axial direction low-pressure side outlet opening.
  • a first diaphragm device 46 provided with an annular diaphragm element 48.
  • the diaphragm member 48 has an L-shaped cross-section with an axial profile section 50 and a radial profile section 52. In addition, it has two different system diameters d1, d2 to form a radially inner axial sealing area and to form a radially outer radial sealing area.
  • the axial sealing region is formed by the axial profile section 50, which for this purpose has an outer peripheral contact surface 54.
  • the radial sealing region is formed by the radial profile section 52, which has a radially extending contact surface 56 for this purpose.
  • the radial profile section 52 has an end section 58 which is considered in the direction of flow.
  • the employment is designed corresponding to a blade-side transition radius to the rear projection 16.
  • a radial web surface 60 is provided between the contact surface 54 and the contact surface 56 in the region of the channels 42.
  • the diaphragm element 48 rests with its contact surface 54 on an inner peripheral side bearing surface 62 of a base body side support ring 64 and with its contact surface 56 against a blade side counter surface 66.
  • the web surface 60 is in abutment with a visible radially extending blade-side abutment surface 68, which is arranged starting from the mating surface 66 on the other side of the channel 42 near the bearing surface 62.
  • the diaphragm device 46 has a securing element 70.
  • the securing element 70 is designed as a securing ring or a corresponding stable securing wire and preferably has a prismatic cross section.
  • the retaining ring 70 may also have other cross-sections and, for example, be designed as a C-profile.
  • the diaphragm element 48 has an inner peripheral groove 72, which is formed in an inner circumferential surface 74 facing away from the contact surface 54.
  • the axial profile section 50 is extended rearwardly beyond an extension 76 for enlarging the inner circumferential surface 74.
  • the diaphragm element 48 is arranged with its inner circumferential groove 72 with respect to a corresponding base-body-side outer circumferential groove 78 and the retaining ring 70 is inserted in half into the grooves 72, 78.
  • the diaphragm element 48 is pushed onto the base body 4. Then the diaphragm element 48 is brought circumferentially in its desired position. Subsequently, the locking ring 70 is threaded into the grooves 72, 78. Finally, the locking ring 70 is bent to the peripheral locking end.
  • annular diaphragm member 48 is mounted by means of a clamping element designed as a clamping ring 70 low-pressure side on a main body side support ring 64.
  • the diaphragm element 48 has an L-shaped cross section with an axial profile section 50 and a radial profile section 52. It has two different system diameters d1, d2 for forming a radially inner axial sealing region and for forming a radially outer radial sealing region.
  • the axial sealing region is formed by the axial profile section 50, which for this purpose has an outer peripheral contact surface 54.
  • the radial sealing area is formed by the radial profile section 52, which is a has radially extending contact surface 56, which is arranged in the region of its counter to the flow direction angled end portion 58.
  • an inner peripheral surface 74 remote from the contact surface 54 is provided, which is formed in a stepped manner radially inwards by an angling of an end section 80 of the axial profile section 50.
  • a radial web surface 60 is provided in the middle of the contact surface 54 and the contact surface 56 in the region of the channels 42.
  • the diaphragm element 48 lies with its contact surface 54 on an inner peripheral side bearing surface 62 of the base body side support ring 64 and with its contact surface 56 on a blade side counter surface 66, which is formed in the blade neck side transition region to the rear projection 16.
  • the web surface 66 is in contact with a non-visible radially extending blade-side abutment surface.
  • a sealing element 82 may be arranged in the region of this sealing region.
  • the clamping ring 70 for securing the diaphragm element 48 on the support ring 64 and on the rotor blades 2 is biased radially outwards and has as in FIG. 5 quantifies a correspondingly the inner peripheral surface 74 step-shaped clamping surface 84 and an axial surface 86 for radial guidance.
  • the axial surface 86 cooperates with a radially extending guide surface 88 of a base body portion 90 which extends radially outwardly.
  • the guide surface 88 forms an axial stop for the clamping ring 70, so that it is arranged in the assembled state in the axial direction securely between the angled end portion 80 of the axial profile section 50 of the diaphragm member 48 and the base body portion 90.
  • the base body portion 90 defines with its guide surface 88 a peripheral chamber 92 which is open over an unnumbered circumferential gap.
  • the clamping ring 70 is first inserted through the open circumferential gap in the circumferential chamber 92 and against its bias against its base 94 and against the guide surface 88 of the body portion to install the diaphragm device 48 90 pressed. Then it will be like in FIG. 7 shown, the diaphragm member 48 against the flow direction and thus guided from back to front on the base body 4 and in the peripheral chamber 92 until it is in contact with the bearing surface 62 with its contact surface 54. Then the clamping ring 70 is relieved, so he as in FIG.
  • annular diaphragm member 48 is fixed in position by means of a fuse element designed as a plurality of locking pins 70 low pressure side on a base body side support ring 64.
  • the diaphragm element 48 has an L-shaped cross section with an axial profile section 50 and a radial profile section 52. It has two different system diameters d1, d2 for forming a radially inner axial sealing region and for forming a radially outer radial sealing region.
  • the axial sealing region is formed by the axial profile section 50, which for this purpose has an outer peripheral contact surface 54.
  • the radial sealing region is formed by the radial profile section 52, which for this purpose has a radially extending contact surface 56 which is arranged in the region of its end section 58 which is angled away from the flow direction.
  • the diaphragm element 48 In the mounted state, the diaphragm element 48 is mounted with its contact surface 54 on an inner peripheral side bearing surface 62 of the base body side support ring 64 by means of adhesion, in particular a press fit.
  • a sealing element 82 is arranged between the contact surface 56 and a blade-side counter-surface 66.
  • this has a plurality of through holes 96.
  • the through-bores 96 are formed in a profile region 98 of the radial profile section 52 which is offset in the direction of the rotor blades 2 and, in the assembled state, is arranged in alignment with the rotor pins 70 receiving blade bores 100 which are in accordance with FIG FIG. 10 extend into the cavity 34.
  • the blade bores 100 may also be formed as blind holes, which are rounded on the bottom side to avoid stresses.
  • the holes 96, 100 are each inclined to the rotation axis and have a diameter such that the locking pins 70 are fixed with a body portion 102 press-fitted in the blade holes 100 and out with a protruding from the blade holes 100 body portion 104 under clearance fit in the through holes 96 are.
  • the holding elements 106 are guided through the through holes 96 and have an S-shaped cross section with two end portions 108, 110 angled in opposite directions. With the end portion 108 angled in the direction of the axis of rotation, they are hooked to the panel element 48. As in FIG. 11 To recognize they are in the mounted state with their angled in the opposite direction end portion 110 on an end face 112 of the respective locking pin 70 at. Furthermore, in FIG. 11 to recognize that the through holes 96 are provided for receiving the holding elements 106 with a corresponding peripheral extension 114 and thus have no circular cross-section.
  • damping elements 118 fixed in the axial direction, in the contact areas 36 (s. FIG. 2 ) are inserted into a corresponding receptacle 120 between the side surfaces 18, 20 and serve for mutual blade stabilization and damping of blade vibrations.
  • the damping elements 118 act as sealing elements to prevent gas exchange of the hot gas and cooling air streams in the radial direction through the contact regions 36.
  • the diaphragm element 48 in the above-described embodiments is preferably designed in one piece and thus formed as a closed over its circumference 360 ° circular ring shell.
  • the diaphragm elements 48 may also be designed in several parts and consist of, for example, individual diaphragm element arcs which can be joined to the respective annular diaphragm element.
  • the diaphragm device 46 per se can of course also be arranged on the high pressure side or inlet side, as viewed in the flow direction of the hot gas flow in front of the channels 42.
  • an aperture device for an integrally bladed rotor body of a turbomachine for adjusting a cooling air flow from a high pressure side to a low pressure side through channels formed between adjacent blades, with an annular diaphragm member for at least partially covering the channel cross sections, the diaphragm member having two abutment diameters to form a radially inward lying axial sealing region and for forming a radially outer radial sealing region, an integrally bladed rotor body with such a diaphragm device, a method for producing such an integrally bladed rotor body and a turbomachine with such an integrally bladed rotor body.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP11162771A 2011-04-18 2011-04-18 Dispositif de diaphragme, corps de base de rotor à aubage intégral, procédé et turbomachine Withdrawn EP2514923A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP11162771A EP2514923A1 (fr) 2011-04-18 2011-04-18 Dispositif de diaphragme, corps de base de rotor à aubage intégral, procédé et turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP11162771A EP2514923A1 (fr) 2011-04-18 2011-04-18 Dispositif de diaphragme, corps de base de rotor à aubage intégral, procédé et turbomachine

Publications (1)

Publication Number Publication Date
EP2514923A1 true EP2514923A1 (fr) 2012-10-24

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EP11162771A Withdrawn EP2514923A1 (fr) 2011-04-18 2011-04-18 Dispositif de diaphragme, corps de base de rotor à aubage intégral, procédé et turbomachine

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3052762A4 (fr) * 2013-10-03 2017-10-04 United Technologies Corporation Caractéristique permettant de fournir un flux de refroidissement à un disque
US11319823B2 (en) * 2018-02-02 2022-05-03 Siemens Energy Global GmbH & Co. KG Rotor with sealing element and ring seal

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5318405A (en) * 1993-03-17 1994-06-07 General Electric Company Turbine disk interstage seal anti-rotation key through disk dovetail slot
EP1180580A1 (fr) * 2000-08-10 2002-02-20 Snecma Moteurs Dispositif de rétention d'une flasque annulaire contre une face radiale d'un disque à aubes
US20040062643A1 (en) * 2002-09-30 2004-04-01 General Electric Company Turbomachinery blade retention system
EP1439282A1 (fr) * 2003-01-16 2004-07-21 Snecma Moteurs Dispositif pour retenir un flasque annulaire contre une face radiale d'un disque
EP1498579A1 (fr) * 2003-07-17 2005-01-19 Snecma Moteurs Rétention de flasque de rotor
US20050265849A1 (en) * 2004-05-28 2005-12-01 Melvin Bobo Turbine blade retainer seal
EP2184443A1 (fr) * 2008-11-05 2010-05-12 Siemens Aktiengesellschaft Turbine à gaz avec plaque de fixation entre le pied d'aube et le disque
EP2218873A1 (fr) * 2009-02-17 2010-08-18 Siemens Aktiengesellschaft Section de rotor pour un rotor d'une turbomachine, aube directrice pour une turbomachine et élément de blocage
DE102009007468A1 (de) 2009-02-04 2010-08-19 Mtu Aero Engines Gmbh Integral beschaufelte Rotorscheibe für eine Turbine
DE102009011965A1 (de) 2009-03-05 2010-09-09 Mtu Aero Engines Gmbh Integral beschaufelter Rotor für eine Strömungsmaschine

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5318405A (en) * 1993-03-17 1994-06-07 General Electric Company Turbine disk interstage seal anti-rotation key through disk dovetail slot
EP1180580A1 (fr) * 2000-08-10 2002-02-20 Snecma Moteurs Dispositif de rétention d'une flasque annulaire contre une face radiale d'un disque à aubes
US20040062643A1 (en) * 2002-09-30 2004-04-01 General Electric Company Turbomachinery blade retention system
EP1439282A1 (fr) * 2003-01-16 2004-07-21 Snecma Moteurs Dispositif pour retenir un flasque annulaire contre une face radiale d'un disque
EP1498579A1 (fr) * 2003-07-17 2005-01-19 Snecma Moteurs Rétention de flasque de rotor
US20050265849A1 (en) * 2004-05-28 2005-12-01 Melvin Bobo Turbine blade retainer seal
EP2184443A1 (fr) * 2008-11-05 2010-05-12 Siemens Aktiengesellschaft Turbine à gaz avec plaque de fixation entre le pied d'aube et le disque
DE102009007468A1 (de) 2009-02-04 2010-08-19 Mtu Aero Engines Gmbh Integral beschaufelte Rotorscheibe für eine Turbine
EP2218873A1 (fr) * 2009-02-17 2010-08-18 Siemens Aktiengesellschaft Section de rotor pour un rotor d'une turbomachine, aube directrice pour une turbomachine et élément de blocage
DE102009011965A1 (de) 2009-03-05 2010-09-09 Mtu Aero Engines Gmbh Integral beschaufelter Rotor für eine Strömungsmaschine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3052762A4 (fr) * 2013-10-03 2017-10-04 United Technologies Corporation Caractéristique permettant de fournir un flux de refroidissement à un disque
US10822952B2 (en) 2013-10-03 2020-11-03 Raytheon Technologies Corporation Feature to provide cooling flow to disk
US11319823B2 (en) * 2018-02-02 2022-05-03 Siemens Energy Global GmbH & Co. KG Rotor with sealing element and ring seal

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