RU2537997C2 - Turbomachine stator blade circular sector and aircraft turbomachine - Google Patents

Turbomachine stator blade circular sector and aircraft turbomachine Download PDF

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Publication number
RU2537997C2
RU2537997C2 RU2012107522/06A RU2012107522A RU2537997C2 RU 2537997 C2 RU2537997 C2 RU 2537997C2 RU 2012107522/06 A RU2012107522/06 A RU 2012107522/06A RU 2012107522 A RU2012107522 A RU 2012107522A RU 2537997 C2 RU2537997 C2 RU 2537997C2
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RU
Russia
Prior art keywords
sector
shell
wedge
elementary sectors
sectors
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Application number
RU2012107522/06A
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Russian (ru)
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RU2012107522A (en
Inventor
Лоран Жиль ДЕЗУШ
Патрик Эдмон КАПАЛА
Самир ЗЭДИ
Original Assignee
Снекма
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Publication date
Priority to FR0955439 priority Critical
Priority to FR0955439A priority patent/FR2948736B1/en
Application filed by Снекма filed Critical Снекма
Priority to PCT/EP2010/061037 priority patent/WO2011012679A2/en
Publication of RU2012107522A publication Critical patent/RU2012107522A/en
Application granted granted Critical
Publication of RU2537997C2 publication Critical patent/RU2537997C2/en

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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/40Casings; Connections of working fluid
    • F04D29/52Casings; Connections of working fluid for axial pumps
    • F04D29/54Fluid-guiding means, e.g. diffusers
    • F04D29/541Specially adapted for elastic fluid pumps
    • F04D29/542Bladed diffusers
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D11/00Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/04Antivibration arrangements
    • F01D25/06Antivibration arrangements for preventing blade vibration
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246Fastening of diaphragms or stator-rings
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/60Mounting; Assembling; Disassembling
    • F04D29/64Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/66Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/668Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps damping or preventing mechanical vibrations
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00Stators
    • F01D9/02Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Abstract

FIELD: transport.
SUBSTANCE: this circular sector has inner shell sector, set of blades and assy that makes the outer shell sector. Blades are secured to said assy making the outer shell sector and to inner shell sector. Said assy making the outer shell sector comprises multiple elementary sectors spaced apart along the assy tangential direction and damping wedges. Every damping wedge is fitted between two elementary sectors arranged directly along said tangential direction. Profile of every damping wedge approximates to that of elementary sectors. Damping wedges extend along inclined position of aforesaid assy. Another invention of this set relates to turbomachine including said blade circular sector.
EFFECT: better damping properties.
5 cl, 8 dwg

Description

The invention generally relates to an aircraft turbomachine, preferably a turbojet or turboprop type.

More specifically, the invention relates to a compressor or turbine stator of such a turbomachine, and more particularly, to a blade annular sector comprising a plurality of stator vanes and two concentric shell supporting vanes intended to radially restrict the inside and outside of the main flow passing through the turbomachine. Such a blade ring is usually made using several spread end-to-end sectors, most of which is used in a compressor or turbine as a guiding device or nozzle.

Turbomachines typically comprise a low pressure compressor, a high pressure compressor, a combustion chamber, a high pressure turbine and a low pressure turbine. Compressors and turbines contain several rows of movable blades spaced around the circumference, and these rows are separated by rows of stationary blades, also spaced around the circumference. In modern turbomachines, significant dynamic loads are applied to the guiding devices and nozzles. Technological progress leads to a reduction in the number of stages to ensure equivalent or better performance, which results in a greater load on each stage. Moreover, changes in production technologies lead to a decrease in the number of parts, which reduces the damping effect of the joints between the parts. This is partly a case in which the technology of soldering a wear cartridge is applied, which eliminates a significant source of dispersion of vibration.

The document FR-A-2902843 discloses a means for solving this vibration problem due to the fact that the outer shell sector is divided into elementary sectors located at a fixed distance from each other along the tangential direction through the use of slots or radial cuts in an oblique or other direction, moreover each elementary sector supports one blade of the annular scapular sector. Moreover, damping inserts in the form of plates are inserted between the elementary sectors. The working principle is based on the representation of nonlinear rigidity in the dynamic properties of a structure. Such non-linearity is caused by the presence of a threshold level of system vibration. Such vibrational activity causes a relative movement between the elementary sectors of the blades and the damping inserts. This relative movement causes subsequent loss or adhesion of the damping inserts and, consequently, a continuous change in the local stiffness of the system. Therefore, the mode (s) causing the vibrational activity is suppressed by constantly changing the associated eigenfrequencies. Resonance in a system cannot occur due to a constant change in the state of a dynamic system. This reduces the amplitude of the vibration in the system.

But even though this solution is satisfactory in terms of vibration, it can be improved. Moreover, in such a solution disclosed in the document FR-A-2902843, the damping inserts are kept in contact with the friction surfaces of the elementary sectors due to the pressure difference between the aerodynamic path and the outer part of the compressor, applying force radially inward to these inserts. The disadvantage is that this pressure differential cannot be sufficient to satisfactorily press the inserts into contact with the friction surfaces. In this case, the result is, first of all, a decrease in the vibration damping performance, but a leak in the air duct is also possible.

Another disadvantage of this solution is that one of the blades of the scapular annular sector will be overloaded. The aerodynamic forces applied to the blades include a tangential component, which cannot be resisted in the outer shell sector, due to its segmentation into tangentially spaced elementary sectors. Thus, the tangential components are combined and pass through the sector of the inner shell of the blade ring sector to the blade located adjacent to the anti-rotation stopper mounted on the ring sector. Therefore, this blade is very heavily loaded due to the inability of the outer shell sector to transmit static forces along the tangential direction.

Therefore, it is an object of this invention to at least partially overcome the disadvantages mentioned above that arise in the embodiments according to the prior art.

The first objective of the invention to achieve this is the assembly forming the outer shell sector for the blade annular sector, which will be used on the stator of the compressor or turbine of the aircraft turbomachine, and said outer shell sector, firstly, contains many elementary sectors at a distance from each other along the tangential direction of the aforementioned assembly, and secondly, vibration-damping wedges, each of which is inserted between two elementary sectors associated with him placed directly sequentially along the tangential direction.

According to the invention, the profile of each vibration damping wedge is approximately the same as the profile of elementary sectors.

Due to such a specific profile of the wedges, the frictional contact surface between the wedges and the elementary sectors is large, which results in an improvement in the damping effect.

Moreover, the fact that the wedges are brought into contact with the friction surfaces of the elementary sectors can lead to an ideal seal between these elements, regardless of the pressure difference between the aerodynamic flow path and the outer part of the compressor or turbine. This seal is obtained due to the construction, with wedges applying forces to the friction surfaces of elementary sectors approximately along the tangential direction. Note that this seal is further enhanced during operation, since the forces that bring the friction surfaces and wedges into contact with each other are amplified by the use of the tangential component of the aerodynamic forces applied to the stator vanes of the elementary sectors.

Taking into account the tangential component of the aerodynamic forces applied to the blades, we note that one of the significant advantages of this invention is that this component can pass through the assembly forming the outer shell sector, since the outer shell sector is very rigid along the tangential direction from - due to the specific location of vibration damping wedges, despite the fact that it is divided into sectors along this direction. The result is that the blades are not overloaded, therefore, they are approximately uniformly loaded.

In conclusion, we note that when applying approximately the same profile as elementary sectors, between elementary sectors at a distance from each other, the external radial restriction of the main annular flow, called the air duct, is completely recreated.

Preferably, said wedge is in contact with two parallel planar friction surfaces facing each other along said tangential direction and provided on said two elementary sectors associated with said wedge, said wedge having two complementary planar friction surfaces parallel to each other and interacting with two corresponding friction surfaces of elementary sectors. The plane of contact between the friction surfaces and the complementary friction surfaces gives satisfactory vibration damping by friction. In addition, two friction surfaces can be produced simultaneously during one machining operation, for example, by means of one cutting operation in order to obtain straight slots, in other words, slots in a given plane, inside which corresponding wedges will subsequently be placed. This makes it much easier to manufacture the assembly according to the invention, which leads to significant cost and time savings.

Preferably, said wedge is provided with hooks in order to be held in place on the stator of the compressor or turbine, therefore, these hooks have the same profile as the hooks fixed on elementary sectors.

Preferably, the elementary sectors are separated from each other by radial slots completely filled with said vibration damping wedges.

Preferably, said vibration damping wedges extend approximately along the axial or inclined direction of said assembly.

Another objective of this invention relates to a blade annular sector, designed to be installed on the stator of a compressor or turbine of an aircraft turbomachine, comprising an assembly forming an outer shell sector similar to that described above, an inner shell sector and a plurality of blades tangentially separated from each other, which are inserted between the assembly forming the outer shell sector and the inner shell sector. In this case, each elementary sector will carry one stator blade or, possibly, several blades, without leaving the scope of the invention.

The blade ring may form a compressor guide or turbine nozzle.

Moreover, the annular sector preferably extends over an angular range between 5 and 60 °, but can also be 360 °, forming an entire blade ring.

Another object of the invention is an aircraft turbomachine comprising a compressor or turbine stator equipped with at least one blade annular sector similar to that described above.

Other advantages and characteristics of the invention will become apparent from the detailed non-limiting description below.

This description will be made with reference to the accompanying drawings, in which:

- in FIG. 1 is a schematic sectional view of a turbomachine that will be equipped with one or more blade annular sectors according to this invention;

in FIG. 2 is a sectional view showing a part of the high pressure compressor of the turbomachine shown in FIG. 1, and it includes a scapular annular sector according to this invention;

- in FIG. 3 is a perspective view of a blade annular sector shown in the previous drawing, the sector being in the form of a preferred embodiment of this invention;

- in FIG. 4 shows an axial projection of a portion of a scapular annular sector shown in the previous drawing;

- in FIG. 5 is a side view along line V-V of FIG. 4, wedges and elementary sectors of the scapular annular sector shown in the previous drawings; and

in FIG. 6a-6c show views schematically showing the various steps in the manufacturing process of the blade annular sector shown in the previous drawings.

In FIG. 1 shows an aircraft turbojet engine 100 to which the invention is applicable. It contains, in order from the entrance direction to the exit direction, a low pressure compressor 2, a high pressure compressor 4, an annular combustion chamber 6, a high pressure turbine 8 and a low pressure turbine 10.

In FIG. 2 shows part of a high pressure compressor 4. As you know, the compressor contains rows of 14 stator blades and rows of 16 rotor blades alternating in an axial direction parallel to the axis 12 of the compressor. The stator vanes 18 distributed circumferentially / tangentially about the axis 12 are included in a part of the stator called the blade ring 20, preferably broken into sectors along the circumferential direction 22. Thus, in the following, we will make reference to the blade ring sector 20, it being understood that this sector 20 preferably extends in the angular range between 5 and 60 °, but may be 360 ° so as to form a complete blade ring.

Consequently, the sector 20, forming part or all of the turbine nozzle or the compressor guide, contains a sector of the inner shell 24 forming an inner surface radially limiting the main annular flow 26 passing through the turbomachine, and this sector 24 of the shell supports the fixed bases of the stator vanes 18. In addition to these blades 18, sector 20 also contains an assembly forming a sector of the outer shell, forming an outer surface that radially limits the main annular flow and supports the fixed upper parts of the blades 18.

In this regard, we note that sector 20 also contains known additional elements installed on the shell sector 24, for example, a radial inner wear coating 29 forming an annular sealing track in contact with a sealing device 31 supported by a rotor stage 16 supporting rotating blades and placed on the downstream side of the sector under consideration 20. Rotary sealing device 31 is a known type of labyrinth or lip seal devices.

In FIG. 3 shows a blade annular sector 20. In the described preferred embodiment, the entire nozzle of the turbine or the entire guide vanes of the compressor are obtained by the butt placement of many of these sectors 20, respectively, each of them forms an angular or circumferential section of this blade ring. The angular sectors 20 (only one of which can be seen in Fig. 3) preferably do not contain any direct rigid mechanical connections connecting them to each other, and their adjacent ends are simply placed so as to face each other with or without a gap .

More specifically, with reference to FIG. 3 and 4, the drawings show that the inner annular sector 24 is made as an integral part and is not segmented. On the other hand, the assembly 28, forming the outer shell sector 28, is segmented into elementary sectors 30 at a distance from each other along the tangential direction 22, due to direct radial or slightly beveled slots 32, thereby creating gaps between directly successive sectors 30. Each slot 32 is made along a median straight line between two directly successive blades 18 in such a way that each elementary sector 30 supports a single fixed stator blade 18. One of the two elementary sectors 30, located at the ends of the sector 20, supports a rotation stopper 33, protruding radially outward, which will interact with the other part of the compressor stator in a known manner.

The assembly 28 also contains a vibration damping wedge 34 located between directly successive elementary sectors 30.

More precisely, each vibration damping wedge 34 is located between two plane parallel friction surfaces 38 facing each other along the tangential direction 22 and provided on the respective tangential ends of the two elementary sectors connected to the wedge facing each other. Similarly, each wedge 34 has two complementary planar friction surfaces 40 parallel to each other, as well as parallel and in contact with two corresponding planar friction surfaces 38 with which they interact.

Therefore, each wedge 34 is squeezed between two directly successive elementary sectors 30 having a shape corresponding to the shape of the friction surfaces 38.

The contact between the two friction surfaces 38, 40 of each pair preferably occurs as soon as the wedge 34 is placed between two associated elementary sectors 30. The wedges 34 thus apply forces oriented approximately along the tangential direction with their complementary flat friction surfaces 40 being in contact with the friction surfaces of 38 elementary sectors. These forces mainly increase during operation with the additional use of the tangential component of the aerodynamic forces applied to the stator blades of elementary sectors.

As schematically shown in FIG. 5, one of the specific features of this invention is that the profile of the wedges 34 is approximately the same as the profile of the elementary sectors, this same profile corresponding to the profile of the outer shell sector. In this disclosure, the profile refers to the general shape of the element when viewed along the tangential direction 22, despite the cross-sectional view shown in FIG. 5.

Thus, the bottom surface 46 of each wedge 34, like the elementary sectors 30, acts as an external radial restriction of the air path. Therefore, the common annular surface of the airway restriction, consisting of a sequence of these surfaces 46 formed on the wedges 34 and sectors 30, is approximately continuous from an aerodynamic point of view, since there is no difference between the successive surfaces.

Each wedge 34 and each sector 30 also contains hooks in order to be held in place on another part of the compressor stator, and more specifically, the locking hook 48 projects forward and the locking hook 50 projects back. As shown in FIG. 2, hooks 48, 50 are placed in respective circular slots 52, 54 provided in another part of the compressor stator to secure sector 20 on this other part of the stator.

These wedges 34, which completely fill the slots 32, perform the function of damping vibrations due to friction in contact with the friction surfaces 38 based on the physical principle described above for the wedges disclosed in FR-A-2902843. They also perform the compaction function and the function that allows the tangential component of aerodynamic forces applied to the stator vanes to pass through them. More generally, in this respect, each wedge 34 is capable of transmitting tangential forces between two elementary sectors 30 between which it is inserted.

The type of materials used for the elementary sectors 30 and the wedges 34 is approximately the same, preferably a metal, and is selected so that wedges are preferably worn out than the elementary sectors 30.

Also note that the ratio between the length of each wedge and the length of each elementary sector along the tangential direction, which also correspond to the thickness, is between 0.5 and 1.

In FIG. 6a-6c show a schematic flowchart for manufacturing a blade annular sector 20. First, as shown in FIG. 6a, a one-piece assembly 100 is manufactured by casting or machining forming an inner shell sector 24, an outer shell sector 28, and a stator blade 18. The next step is the manufacture of straight radial slots 32 on the outer shell sector 28 so as to obtain elementary sectors 30, as shown schematically in FIG. 6b, due to simple and economical machining. For example, these slots 32 can be made by cutting sector 28.

Finally, in FIG. 6c shows the final stage, which consists of placing the vibration-damping wedges 34 at a location in the slit 32, forming frictional surfaces, due to the simple sliding movement of the wedges into their respective cavities.

Note that it is preferable that the clearance for the sliding fit is accurate, so that it is relatively easy to insert each wedge into its associated slot and at the same time hold the wedge in its slot only due to the compressive force between the two friction surfaces 38.

Obviously, specialists in the art will make various modifications to the invention, as described above using only non-limiting examples.

Claims (5)

1. The scapular ring sector (20), designed to be installed on the stator of the turbomachine of the aircraft, comprising an assembly forming a sector (28) of the outer shell, a sector (24) of the inner shell and a plurality of blades (18) inserted tangentially apart from each other, inserted between an assembly forming an outer shell sector and an inner shell sector, said blades being attached to each assembly forming an outer shell sector and an inner shell sector, said assembly forming an outer sector (28) bechayki contains many elementary sectors (30) at a distance from each other along the tangential direction (22) of the assembly, and vibration damping wedges (34), each of which is inserted between two elementary sectors associated with it, placed directly sequentially along the aforementioned tangential direction
characterized in that the profile of each vibration damping wedge (34) is approximately the same as the profile of elementary sectors (30), and that said vibration damping wedges (34) extend approximately along the oblique direction of said assembly.
2. The sector according to claim 1, characterized in that said wedge is brought into contact with two parallel planar friction surfaces (38) facing each other along said tangential direction (22) and provided respectively on said two elementary sectors (30), associated with said wedge, and the fact that said wedge (34) has two complementary flat friction surfaces (40) parallel to each other and interacting with two corresponding friction surfaces of elementary sectors.
3. The sector according to claim 1, characterized in that the said wedge (34) is provided with hooks (48, 50) to hold it in place on the compressor or turbine stator.
4. The sector according to claim 1, characterized in that the elementary sectors (30) are separated from each other by radial slots (32), completely filled with said vibration-damping wedges (34).
5. Aircraft turbomachine containing a compressor stator equipped with at least one blade annular sector according to claim 1.
RU2012107522/06A 2009-07-31 2010-07-29 Turbomachine stator blade circular sector and aircraft turbomachine RU2537997C2 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
FR0955439 2009-07-31
FR0955439A FR2948736B1 (en) 2009-07-31 2009-07-31 External virole sector for airborne turbomachine airborne stator crown, comprising shock absorbing mounts
PCT/EP2010/061037 WO2011012679A2 (en) 2009-07-31 2010-07-29 Outer shell sector for a bladed stator ring of an aircraft turbine engine, comprising vibration-damping blocks

Publications (2)

Publication Number Publication Date
RU2012107522A RU2012107522A (en) 2013-09-10
RU2537997C2 true RU2537997C2 (en) 2015-01-10

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RU2012107522/06A RU2537997C2 (en) 2009-07-31 2010-07-29 Turbomachine stator blade circular sector and aircraft turbomachine

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US (1) US20120128482A1 (en)
EP (1) EP2459884B1 (en)
JP (1) JP5697667B2 (en)
CN (1) CN102472297A (en)
BR (1) BR112012002304A2 (en)
CA (1) CA2769217A1 (en)
FR (1) FR2948736B1 (en)
RU (1) RU2537997C2 (en)
WO (1) WO2011012679A2 (en)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2971022B1 (en) 2011-02-02 2013-01-04 Snecma Compressor rectifier stage for a turbomachine
US9610644B2 (en) * 2011-02-08 2017-04-04 United Technologies Corporation Mate face brazing for turbine components
US9546557B2 (en) * 2012-06-29 2017-01-17 General Electric Company Nozzle, a nozzle hanger, and a ceramic to metal attachment system
US9334756B2 (en) 2012-09-28 2016-05-10 United Technologies Corporation Liner and method of assembly
WO2014197035A2 (en) 2013-03-15 2014-12-11 United Technologies Corporation Acoustic liner with varied properties
DE102013212252A1 (en) * 2013-06-26 2014-12-31 Siemens Aktiengesellschaft Turbine and method of squeal detection
FR3008455B1 (en) * 2013-07-09 2015-08-21 Snecma Compressor rectifier having game retrieval means
CN104440153B (en) * 2014-11-04 2017-06-06 中国南方航空工业(集团)有限公司 Casing intra vane processes damping unit
FR3029242B1 (en) 2014-11-28 2016-12-30 Snecma TURBOMACHINE TURBINE, COMPRISING INTERCROSSED PARTITIONS FOR AIR CIRCULATION IN DIRECTION OF THE LEAK EDGE
US10655482B2 (en) * 2015-02-05 2020-05-19 Rolls-Royce Corporation Vane assemblies for gas turbine engines
CN106988794B (en) * 2017-06-02 2018-12-14 中国航发南方工业有限公司 Stator sub-assembly clamping means and stator sub-assembly
CN107747563B (en) * 2017-09-30 2020-04-10 中国航发沈阳发动机研究所 Fan casing with damping

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU453486A1 (en) * 1973-04-11 1974-12-15 Device for damping the oscillations of work bladdes of axial turbo dumpers
US5201850A (en) * 1991-02-15 1993-04-13 General Electric Company Rotor tip shroud damper including damper wires
US6733237B2 (en) * 2002-04-02 2004-05-11 Watson Cogeneration Company Method and apparatus for mounting stator blades in axial flow compressors
FR2902843A1 (en) * 2006-06-23 2007-12-28 Snecma Sa Compressor rectifier area or turbomachine distributor sector

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2661147A (en) * 1949-01-19 1953-12-01 Ingersoll Rand Co Blower blade fastening device
JPS5641802B2 (en) * 1975-09-25 1981-09-30
DE4436731A1 (en) * 1994-10-14 1996-04-18 Abb Management Ag Compressor
FR2831615B1 (en) * 2001-10-31 2004-01-02 Snecma Moteurs Sectorized fixed rectifier for a turbomachine compressor
US6984108B2 (en) * 2002-02-22 2006-01-10 Drs Power Technology Inc. Compressor stator vane
EP1510654A1 (en) * 2003-08-25 2005-03-02 Siemens Aktiengesellschaft Unitary turbine blade array and method to produce the unitary turbine blade array.
US7104752B2 (en) * 2004-10-28 2006-09-12 Florida Turbine Technologies, Inc. Braided wire damper for segmented stator/rotor and method
US7591634B2 (en) * 2006-11-21 2009-09-22 General Electric Company Stator shim welding
US7806655B2 (en) * 2007-02-27 2010-10-05 General Electric Company Method and apparatus for assembling blade shims

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SU453486A1 (en) * 1973-04-11 1974-12-15 Device for damping the oscillations of work bladdes of axial turbo dumpers
US5201850A (en) * 1991-02-15 1993-04-13 General Electric Company Rotor tip shroud damper including damper wires
US6733237B2 (en) * 2002-04-02 2004-05-11 Watson Cogeneration Company Method and apparatus for mounting stator blades in axial flow compressors
FR2902843A1 (en) * 2006-06-23 2007-12-28 Snecma Sa Compressor rectifier area or turbomachine distributor sector

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Publication number Publication date
FR2948736B1 (en) 2011-09-23
US20120128482A1 (en) 2012-05-24
FR2948736A1 (en) 2011-02-04
JP5697667B2 (en) 2015-04-08
WO2011012679A2 (en) 2011-02-03
CN102472297A (en) 2012-05-23
BR112012002304A2 (en) 2016-05-31
CA2769217A1 (en) 2011-02-03
RU2012107522A (en) 2013-09-10
JP2013501181A (en) 2013-01-10
EP2459884B1 (en) 2018-06-27
EP2459884A2 (en) 2012-06-06
WO2011012679A3 (en) 2011-04-21

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