US20150176417A1 - Blade ring for a turbomachine - Google Patents

Blade ring for a turbomachine Download PDF

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Publication number
US20150176417A1
US20150176417A1 US14/415,590 US201314415590A US2015176417A1 US 20150176417 A1 US20150176417 A1 US 20150176417A1 US 201314415590 A US201314415590 A US 201314415590A US 2015176417 A1 US2015176417 A1 US 2015176417A1
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US
United States
Prior art keywords
blade
wedge
shaped clamping
clamping element
groove
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.)
Abandoned
Application number
US14/415,590
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English (en)
Inventor
Dimitri Zelmer
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
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Zelmer, Dimitri
Publication of US20150176417A1 publication Critical patent/US20150176417A1/en
Abandoned 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
    • 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
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/322—Blade mountings

Definitions

  • the invention relates to a blade ring for an axial turbomachine, comprising a blade carrier having a number of retaining grooves—having support flanks—for blades and a corresponding number of blades, the blade roots of which, which are configured in a manner corresponding to the retaining grooves, are inserted into the retaining grooves, wherein the blades have, on the blade root underside thereof facing toward a groove base of the retaining groove, a recess, the base of which is at least partially obliquely inclined with respect to the groove base of the retaining groove and in which there is arranged in each case a wedge-shaped clamping element for pressing the blade root against the support flanks.
  • a subject matter of the generic type is known, for example, from EP 1 892 380 A1.
  • two wedges are provided for each rotor blade between a blade root underside and the groove base of the retaining groove.
  • the inclinations of the two wedges are in this case opposite.
  • a clamping screw is screwed into the end of each wedge, making it possible on the one hand to achieve a radial prestressed positioning of the blade roots on corresponding support flanks of the retaining grooves.
  • the screwed connection also serves to fix the rotor blades along the retaining grooves. Resilient fastening of the rotor blades is achieved by virtue of the fact that disk springs can be provided beneath the wedges.
  • a securing plate is positioned between the blade root and the retaining groove on the groove base. Through a bead on the securing plate, the latter engages into an opening provided on the root. After the blade has been inserted with the securing plate and the surrounding ends have been bent at the inlet and outlet sides of the root, form-fitting securing is achieved. In order to make it possible to ensure a sufficiently prestressed fit of the blade in the groove during operation, it is also necessary for the blade to be mounted with a prestress.
  • each recess is provided with a spring element, the spring force of which acts along the retaining groove on the respective wedge-shaped clamping element, wherein the recess is delimited by a first side wall and a second wall located opposite the first side wall, wherein the spring element is
  • the spring element presses the wedge-shaped clamping element in the direction of its acute end, as a result of which, in combination with the inclined base of the recess, a force acts in the radial direction (with respect to the installed position in an axial turbomachine) on the blade root, pressing the latter against the support flanks of the retaining grooves.
  • the spring element is therefore supported on the one hand on a first side wall of the recess and on the other hand on the obtuse end of the wedge-shaped clamping element.
  • the magnitude of the spring force can be achieved by a simple variation of different spring elements. This is the case particularly when the spring elements are configured as disk springs or disk spring assemblies. At the same time, it is possible for the tolerance of the connection between the blade and blade carrier to be lowered to an average measure, making it possible to produce the components in a comparatively inexpensive manner.
  • this prestressing device is constantly adapted to the radial position of the blade.
  • the blade When formed from rotor blade rings, the blade will assume its maximum radial position in the retaining groove during operation under the action of the centrifugal forces.
  • the wedge-shaped clamping element In parallel therewith, the wedge-shaped clamping element is pressed in further beneath the blade under the action of the spring force of the spring element. Therefore, a particularly high prestress of the blade is retained even when the rotational speed of the machine decreases. This limits the relative movements even of comparatively large blades and reduces the wear in the retaining grooves.
  • the spring element is in the form of a disk spring or disk spring assembly.
  • an opening is provided in the first side wall.
  • a cylindrical pin is arranged at the obtuse end of the wedge-shaped clamping element and extends both through the disk spring or the disk spring assembly and into the opening or through the opening in the side wall.
  • the cylindrical pin can be driven into a bore arranged on the clamping element or can be firmly adhesively bonded there.
  • the cylindrical pin has the function of guiding the spring element and at the same time of securing the wedge-shaped clamping element, so that the latter cannot undesirably jump out of the recess during mounting.
  • the means comprises a threaded hole, which is arranged in the second side wall and into which a mounting screw can be screwed from the outside to displace the wedge-shaped clamping element toward the first side wall. Consequently, firstly the spring element is put over the cylindrical pin of the wedge-shaped clamping element before the blade is mounted, and then the cylindrical pin is introduced into the opening arranged in the first side wall. At the same time, the wedge-shaped clamping element is placed into the recess arranged on the underside of the blade root.
  • a mounting screw having a threaded shank of appropriate length is temporarily screwed in from the outside through the threaded hole present in the second side wall, said mounting screw making it possible for the wedge-shaped clamping element to be displaced in the direction of the first side wall.
  • the displacement here has to be effected to such an extent that the wedge-shaped clamping element is countersunk completely in the recess, and mounting of the blade with the clamping element with play is thus possible.
  • the subassembly produced in this way is pushed into the retaining groove.
  • the mounting screw screwed into the second side wall can be released again, as a result of which the wedge-shaped clamping element is pressed in the direction of the second side wall by the spring element.
  • the wedge-shaped clamping element is pressed into the narrowing space between the groove base and the base, and comes to rest against both faces—the groove base and the base.
  • the blade root is then braced against the support flanks of the retaining groove.
  • a bayonet connection instead of a threaded connection in the second side wall, it is also possible for a bayonet connection to be provided, for example.
  • a plate-like securing element arranged between a blade root underside and a groove base of the retaining groove lying opposite the blade root underside secures each of the blades against displacement along the retaining grooves, in that the ends of the plate-like securing element bear laterally against the blade carrier.
  • the plate-like securing element is located between the groove base and the wedge-shaped clamping element.
  • the wedge-shaped clamping element has an at least partially hollow form. This makes the fastening of the blade more elastic in the direction of prestress and additionally makes frictional damping possible.
  • the blade ring is a rotor blade ring, and therefore the blade carrier is in the form of a rotor disk or shaft and the blade is in the form of a rotor blade. Nevertheless, the blade ring is also suitable for fastening guide blades.
  • FIG. 1 shows a stationary gas turbine in a longitudinal partial section
  • FIG. 2 shows the longitudinal section through a blade ring in the region of a retaining groove with a blade inserted therein according to a first exemplary embodiment
  • FIG. 3 shows the side view of the section shown in FIG. 2 .
  • FIG. 4 shows a further side view of a retaining groove with a blade inserted therein
  • FIG. 5 shows a longitudinal section analogous to FIG. 2 for a second exemplary embodiment of a blade ring.
  • FIG. 1 shows a stationary gas turbine 10 in a longitudinal partial section.
  • the gas turbine 10 has, in the interior, a rotor 14 , which is mounted rotatably about an axis of rotation 12 and which is also referred to as a turbine rotor.
  • An intake housing 16 , a compressor 18 , a toroidal annular combustion chamber 20 with a plurality of burners 22 arranged rotationally symmetrically to one another, a turbine unit 24 and a turbine outlet housing 26 follow one another along the rotor 14 .
  • the compressor 18 comprises an annular compressor duct with compressor stages following one another in cascade in the latter and composed of rotor blade and guide blade rings 44 .
  • the rotor blades 17 arranged on the rotor 14 are supported by rotor disks and lie with their freely ending airfoil tips 29 opposite an outer duct wall 42 of the compressor duct.
  • the compressor duct issues via a compressor outlet diffuser 36 in a plenum 38 .
  • the annular combustion chamber 20 with its combustion space 28 , which communicates with an annular hot gas duct 30 of the turbine unit 24 .
  • Four turbine stages 32 connected in series are arranged in the turbine unit 24 .
  • a generator or a working machine (not illustrated in either case) is coupled to the rotor 14 .
  • the compressor 18 When the gas turbine 10 is in operation, the compressor 18 sucks in through the intake housing 16 ambient air 34 as the medium to be compressed and compresses this ambient air.
  • the compressed air is routed through the compressor outlet diffuser 36 into the plenum 38 , from where it flows into the burners 22 .
  • Fuel also passes via the burners 22 into the combustion space 28 .
  • the fuel is burnt there, with the addition of the compressed air, to form a hot gas M.
  • the hot gas M subsequently flows into the hot gas duct 30 , where it expands, so as to perform work, at the turbine blades of the turbine unit 24 .
  • the energy released in the meantime is absorbed by the rotor 14 and is utilized, on the one hand, for driving the compressor 18 and, on the other hand, for driving a working machine or electric generator.
  • FIG. 2 shows a section through a rotor disk 19 of the rotor 14 of the gas turbine 10 in the region of a retaining groove 21 extending in the axial direction.
  • the rotor disk 19 therefore represents a blade carrier 46 , in the case of which the retaining grooves 21 are distributed uniformly along the circumference thereof and in this respect extend in the axial direction of the gas turbine.
  • the retaining grooves 21 have a dovetail-like cross section ( FIG. 3 , FIG. 4 ) and therefore each comprise two support flanks 23 , against which correspondingly configured bearing surfaces 25 of a blade root 31 of the blades 27 bear.
  • the blades 27 are in the form of rotor blades.
  • a recess 37 is provided on an underside 33 of the blade root 31 which faces toward a groove base 35 of the retaining groove 21 .
  • the recess 37 is delimited by a first side wall 39 and a second side wall 41 lying opposite the first side wall 39 .
  • the first side wall 39 is arranged on the inflow side and the second side wall 41 is arranged on the outflow side.
  • a plate-like securing element 43 with longitudinally slotted ends is placed in the retaining groove 21 between the underside 33 and the groove base 35 .
  • a tab 45 is bent outward and a tab 45 is bent inward ( FIGS. 3 and 4 ), blocking displacement of the blade 27 inserted in the retaining groove 21 .
  • a wedge-shaped clamping element 47 having an acute end 49 and an obtuse end 51 is provided in the recess 37 .
  • a cylindrical pin 53 Arranged at the obtuse end 51 is a cylindrical pin 53 , onto which a total of four disk springs are threaded as a spring element 55 in the exemplary embodiment shown.
  • the cylindrical pin 53 extends into an opening 57 arranged in the first side wall 39 .
  • the base 59 of the recess 37 is inclined with respect to the groove base 35 of the retaining groove 21 , corresponding to the inclination of the upper face 61 of the wedge-shaped clamping element 47 as shown in FIG. 2 .
  • a threaded hole 63 is provided in the second side wall 41 and—like the opening 57 —extends parallel to the retaining groove 21 .
  • a mounting screw 65 required for mounting the blade 27 can be screwed into the threaded hole 63 and can be used to displace the wedge-shaped clamping element 47 to the left in FIG. 2 to such an extent that the obtuse end 51 thereof is positioned comparatively close to the first side wall 39 .
  • the wedge-shaped clamping element 47 can thereby be countersunk completely in the recess 37 .
  • the blade 27 is then mounted in the retaining groove 21 as follows: firstly, the prefabricated plate-like securing element 43 is inserted into the retaining groove.
  • the plate-like securing element 43 extends over the entire length of the retaining groove 21 , with two of the tabs 45 already being bent on the inflow side or outflow side transversely to the longitudinal extent thereof.
  • the outwardly bent tab 45 serves as a stop when the blade 27 is being pushed into the retaining groove 21 .
  • At the other end of the plate-like securing element 43 for the time being only one of the two tabs 45 is pre-bent in the radial direction toward the machine axis.
  • the spring element 55 is placed onto the cylindrical pin 53 of the wedge-shaped clamping element 47 , and these are inserted together into the opening 57 and the recess 37 .
  • the cylindrical pin 53 then engages into the opening 57 , which is in the form of an elongated hole.
  • the mounting screw 65 is then screwed into the threaded hole 63 , to such a depth that the wedge-shaped clamping element 47 is pressed toward the opposite side, i.e. in the direction of the first side wall 39 , to be precise until the wedge base 67 is located within the recess. It is thereby possible to ensure the insertion of the blade 27 without prestress.
  • the blade 27 is pushed into the retaining groove 21 with the prestressed wedge-shaped clamping element 47 .
  • the mounting screw 65 is released and removed from the subassembly.
  • the wedge-shaped clamping element 47 is relieved of the force of the mounting screw and, through the action of the axial forces of the spring element 55 , can press the blade 27 in the retaining groove 21 against the support flanks 23 thereof, and thus prestress it.
  • the tab 45 of the plate-like securing element 43 which hitherto has not been bent is bent in the radial direction away from the machine axis, and this then secures the blade 27 against escaping from the retaining groove 21 .
  • the working steps are to be carried out in a reverse order.
  • the mounting screw 65 is to be screwed into the threaded hole 63 .
  • the prestress is released and the blade 27 is relieved of load, after which it can then be easily pushed out of the retaining groove 21 .
  • the wedge-shaped clamping element 47 can have an at least partially hollow form.
  • the hollow space 69 brings about an elastic prestress and therefore additionally involves frictional damping.
  • the invention relates to a blade ring 44 for an axial turbomachine, comprising a blade carrier 46 having a number of retaining grooves 21 and a corresponding number of blades 27 , the blade roots 31 of which are inserted into the retaining grooves 21 , wherein the blades 27 each have, on the underside 33 thereof facing toward a groove base 35 of the retaining groove 21 , a recess 37 , the base 59 of which is at least partially obliquely inclined with respect to the groove base 35 of the retaining groove 21 and in which there is arranged in each case a wedge-shaped clamping element 47 for pressing the blade root 31 against the support flanks 23 .
  • each recess 37 is provided with a spring element 55 , the spring force of which acts along the retaining groove 21 on the respective wedge-shaped clamping element 47 , and that provision is made of means with which, for mounting the blade 27 in the retaining groove 21 without prestress, the wedge-shaped clamping element 47 can be displaced temporarily into a position in which the blade root 31 sits in the retaining groove 21 without prestress.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US14/415,590 2012-07-27 2013-07-29 Blade ring for a turbomachine Abandoned US20150176417A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE102012213227.9 2012-07-27
DE102012213227A DE102012213227B3 (de) 2012-07-27 2012-07-27 Schaufelkranz für eine Turbomaschine
PCT/EP2013/065885 WO2014016431A1 (de) 2012-07-27 2013-07-29 Schaufelkranz für eine turbomaschine

Publications (1)

Publication Number Publication Date
US20150176417A1 true US20150176417A1 (en) 2015-06-25

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Application Number Title Priority Date Filing Date
US14/415,590 Abandoned US20150176417A1 (en) 2012-07-27 2013-07-29 Blade ring for a turbomachine

Country Status (8)

Country Link
US (1) US20150176417A1 (zh)
EP (1) EP2867478B1 (zh)
JP (1) JP5934443B2 (zh)
KR (1) KR20150037864A (zh)
CN (1) CN104508248B (zh)
DE (1) DE102012213227B3 (zh)
RU (1) RU2015106789A (zh)
WO (1) WO2014016431A1 (zh)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150315934A1 (en) * 2012-09-19 2015-11-05 Siemens Aktiengesellschaft Device for overcoming play
US20170284202A1 (en) * 2016-04-05 2017-10-05 United Technologies Corporation Fan blade removal feature for a gas turbine engine
WO2017205246A1 (en) * 2016-05-27 2017-11-30 General Electric Company Margin bucket dovetail radial support feature for axial entry buckets
FR3084162A1 (fr) * 2018-07-23 2020-01-24 Safran Aircraft Engines Montage d'essai, et machine de test en fatigue vibratoire.
US10669868B2 (en) 2016-12-22 2020-06-02 Nuovo Pignone Tecnologie Srl Turbine blade and locking set
CN112483464A (zh) * 2020-10-27 2021-03-12 中国船舶重工集团公司第七0三研究所 一种新型周向槽型燃气轮机压气机叶片锁紧装置
CN114109902A (zh) * 2020-08-25 2022-03-01 通用电气公司 叶片燕尾榫和保持设备
US11555407B2 (en) 2020-05-19 2023-01-17 General Electric Company Turbomachine rotor assembly
US11603794B2 (en) 2015-12-30 2023-03-14 Leonard Morgensen Andersen Method and apparatus for increasing useful energy/thrust of a gas turbine engine by one or more rotating fluid moving (agitator) pieces due to formation of a defined steam region
FR3140120A1 (fr) * 2022-09-22 2024-03-29 Safran Aircraft Engines Roue de turbine comprenant un dispositif de retenue axiale de pieds d’aube dans les alvéoles d’un disque
US12065948B1 (en) * 2023-06-09 2024-08-20 Rtx Corporation Blade spacer

Families Citing this family (5)

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Publication number Priority date Publication date Assignee Title
US9739160B2 (en) 2013-10-18 2017-08-22 Siemens Aktiengesellschaft Adjustable blade root spring for turbine blade fixation in turbomachinery
CN109113798A (zh) * 2018-08-27 2019-01-01 广东惠州天然气发电有限公司 一种新型燃气轮机静叶环
CN110439858B (zh) * 2019-09-09 2024-10-18 上海电气燃气轮机有限公司 一种具有减振效果的叶片锁紧结构
CN111946642B (zh) * 2020-08-17 2021-06-29 江苏恒康机电有限公司 一种方便拆卸的不锈钢风机
FR3121954B1 (fr) * 2021-04-20 2023-07-14 Safran Aircraft Engines Dispositif de calage d’un pied d’aube dans une alveole d’un disque de rotor de turbomachine

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US8439635B2 (en) * 2009-05-11 2013-05-14 Rolls-Royce Corporation Apparatus and method for locking a composite component

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EP1507958A1 (de) * 2002-05-24 2005-02-23 ABB Turbo Systems AG Axialsicherung fuer laufschaufeln
DE502005000782D1 (de) * 2005-03-17 2007-07-12 Siemens Ag Biegevorrichtung und Verfahren zum Biegen eines Sicherungsbleches in einem Verdichter oder einer Turbine
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US5123813A (en) * 1991-03-01 1992-06-23 General Electric Company Apparatus for preloading an airfoil blade in a gas turbine engine
US8439635B2 (en) * 2009-05-11 2013-05-14 Rolls-Royce Corporation Apparatus and method for locking a composite component

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150315934A1 (en) * 2012-09-19 2015-11-05 Siemens Aktiengesellschaft Device for overcoming play
US11603794B2 (en) 2015-12-30 2023-03-14 Leonard Morgensen Andersen Method and apparatus for increasing useful energy/thrust of a gas turbine engine by one or more rotating fluid moving (agitator) pieces due to formation of a defined steam region
US20170284202A1 (en) * 2016-04-05 2017-10-05 United Technologies Corporation Fan blade removal feature for a gas turbine engine
US10208709B2 (en) * 2016-04-05 2019-02-19 United Technologies Corporation Fan blade removal feature for a gas turbine engine
WO2017205246A1 (en) * 2016-05-27 2017-11-30 General Electric Company Margin bucket dovetail radial support feature for axial entry buckets
US10465537B2 (en) 2016-05-27 2019-11-05 General Electric Company Margin bucket dovetail radial support feature for axial entry buckets
US10669868B2 (en) 2016-12-22 2020-06-02 Nuovo Pignone Tecnologie Srl Turbine blade and locking set
FR3084162A1 (fr) * 2018-07-23 2020-01-24 Safran Aircraft Engines Montage d'essai, et machine de test en fatigue vibratoire.
US11555407B2 (en) 2020-05-19 2023-01-17 General Electric Company Turbomachine rotor assembly
CN114109902A (zh) * 2020-08-25 2022-03-01 通用电气公司 叶片燕尾榫和保持设备
US11396822B2 (en) 2020-08-25 2022-07-26 General Electric Company Blade dovetail and retention apparatus
US11697996B2 (en) 2020-08-25 2023-07-11 General Electric Company Blade dovetail and retention apparatus
US11834965B2 (en) 2020-08-25 2023-12-05 General Electric Company Blade dovetail and retention apparatus
CN112483464A (zh) * 2020-10-27 2021-03-12 中国船舶重工集团公司第七0三研究所 一种新型周向槽型燃气轮机压气机叶片锁紧装置
FR3140120A1 (fr) * 2022-09-22 2024-03-29 Safran Aircraft Engines Roue de turbine comprenant un dispositif de retenue axiale de pieds d’aube dans les alvéoles d’un disque
US12065948B1 (en) * 2023-06-09 2024-08-20 Rtx Corporation Blade spacer

Also Published As

Publication number Publication date
EP2867478B1 (de) 2016-09-21
CN104508248A (zh) 2015-04-08
CN104508248B (zh) 2016-08-17
KR20150037864A (ko) 2015-04-08
EP2867478A1 (de) 2015-05-06
JP2015524531A (ja) 2015-08-24
WO2014016431A1 (de) 2014-01-30
DE102012213227B3 (de) 2013-09-26
JP5934443B2 (ja) 2016-06-15
RU2015106789A (ru) 2016-09-20

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