EP2636850A1 - Stator des turbines à gaz - Google Patents
Stator des turbines à gaz Download PDFInfo
- Publication number
- EP2636850A1 EP2636850A1 EP13158473.2A EP13158473A EP2636850A1 EP 2636850 A1 EP2636850 A1 EP 2636850A1 EP 13158473 A EP13158473 A EP 13158473A EP 2636850 A1 EP2636850 A1 EP 2636850A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- recess
- insert
- casing
- segments
- 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
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
Definitions
- the subject matter disclosed herein relates to casings for use in various types of rotary systems such as compressors and gas turbines.
- Rotary systems such as compressors and turbines, may generally include a rotor portion that rotates about an axis during the operation of the system as well as a stator portion (e.g., casing, shroud, etc.) that remains substantially immobile during system operation.
- the rotor portion may include a number of blades disposed about a shaft. During operation of the compressor, this shaft may rotate, causing the attached blades to rotate within a stationary casing (i.e., the stator) surrounding the rotor.
- the temperature present within the compressor may be high (e.g., in excess of 1000 °C)
- portions of the rotor and/or casing of the compressor may warm and expand during operation. This expansion may change the clearance between these portions of the rotor and/or casing during operation of the compressor, which may affect the ability of the compressor to properly function and/or operate efficiently.
- a system including a rotary machine.
- the rotary machine includes a rotor having a plurality of blades and a segmented stator having a plurality of stator segments arranged circumferentially about the plurality of blades.
- Each adjacent pair of first and second segments of the plurality of stator segments includes a recess extending circumferentially across an intermediate joint between the first and second segments.
- each recess includes at least one eccentricity control insert configured to mitigate eccentricity of an inner circumference of the segmented stator due to thermal expansion or thermal contraction of the segmented stator.
- a system in another aspect of the invention, includes an eccentricity control insert configured to mount in a recess at an intermediate joint between an adjacent pair of first and second segments of a segmented stator of a rotary machine. Furthermore, the eccentricity control insert is configured to mitigate eccentricity of an inner circumference of the segmented stator due to thermal expansion or thermal contraction of the segmented stator.
- a system in another aspect of the invention, includes a segmented stator including a plurality of stator segments arranged circumferentially about a rotational axis of a rotary machine. Each adjacent pair of first and second segments of the plurality of stator segments includes a recess extending circumferentially across an intermediate joint between the first and second segments. Furthermore, each recess includes at least one eccentricity control insert configured to mitigate eccentricity of an inner circumference of the segmented stator due to thermal expansion or thermal contraction of the segmented stator.
- the temperature of the gases present within a rotary system may be relatively high and/or fluctuate during certain points during the operation of the system. These elevated and fluctuating temperatures in the rotary system may cause portions the casing (i.e., stator) encircling the rotor to warm and expand or cool and contract during system operation. Additionally, since a casing of a rotary system may include a number of coupled segments, then the expansion/contraction of the casing at or near the joints may not be the same as the expansion in the middle of the casing segments.
- the casing e.g., the inner circumference of the casing
- the casing of a rotary system e.g., a compressor or turbine
- portions of rotor and casing may contact one another, resulting in premature wear, vibration, and/or cracking in the rotary system.
- the casing of the rotary system expands and/or contracts in another manner during operation, then clearance between the rotor and the casing may be too great, resulting in reduced efficiency of the rotary system.
- the casing i.e., stator
- the disclosed embodiments employ inserts in recesses along each joint between casing segments, thereby helping to maintain roundness of the casing (e.g., an inner surface of the casing) despite thermal expansion or contraction.
- FIG. 1 is a block diagram of an embodiment of a turbine system 10 that includes two rotary systems (i.e., a compressor and a gas turbine) having an eccentricity control system in accordance with aspects of the present technique. That is, as discussed in detail below, the casings of the rotary systems of the turbine system 10 have been modified to include an eccentricity control insert to help maintain the roundness of the casings despite thermal expansion or contraction.
- the illustrated turbine system 10 includes a gas turbine engine 12 coupled to a load 14, such as an electrical generator.
- the gas turbine engine 12 includes a compressor 16, a plurality of combustors 18 each having at least one fuel nozzle 20, a turbine 22, and an exhaust section 24.
- one or more shafts 26 connect the load 14, compressor 16, and turbine 22.
- the compressor 16 and the turbine 22 each include a rotor with blades, which rotate about a rotational axis 28 within a stator (i.e., casing) that has been modified to mitigate eccentricity during thermal expansion, as discussed in detail below.
- the compressor 16 receives air 30 and delivers compressed air 32 to the combustors 18 and/or fuel nozzles 20, which then injects fuel 34 (or an air-fuel mixture) into a combustion region in the combustors 18.
- the air-fuel mixture combusts in the combustors 18 to produce hot combustion gases 36, which drive blades within the turbine 18.
- the compressor 16 is driven to compress the air 16 into the combustors 18 and/or fuel nozzles 20.
- the axial direction 38 is generally oriented along the rotational axis 28.
- the illustrated compressor 16 and turbine 22 include casings (i.e., stators or shrouds) that have been modified in order to reduce the potential of the casings to expand or contract out of roundness (e.g., become eccentric) during operation of the system 10.
- casings i.e., stators or shrouds
- disclosed embodiments generally have portions of each of the segments of the case absent or removed near the joints (e.g., removed portions where the individual segments of the case meet).
- the removed portions of the segments near the joints may take the form of a recess, a groove, or a slot.
- the disclosed embodiments utilize an insert that may be disposed within the groove or recess to generally control the clearance between the blades of the rotor and the casing of the rotary machine (e.g., compressor 16 or turbine 22). While the various aspects of the modified casing embodiments are described below with respect to the compressor 16, it should be appreciated that the presently disclosed casing embodiments are applicable to the gas turbine 22 or any rotary system where uniform and/or minimized clearance between the rotor and stator are desirable.
- FIG. 2 illustrates a cross-section of an embodiment of the compressor 16 having the modified casing in accordance with aspects of the present technique.
- the illustrated compressor 16 includes a rotor 50 having a number of blades 52 disposed about a shaft 54. Furthermore, the blade 52 of the rotor 50 are configured to rotate (i.e., about the rotational axis 28) within the stator or compressor casing 56.
- the casing 56 of the compressor 16 it is desirable for the casing 56 of the compressor 16 to provide a uniform, minimal clearance 58 between the blades 52 of the rotor 50 and the casing 56. That is, it is generally desirable for the blades 52 of the rotor 50 to come as close as possible to the casing 56 without actually contacting the casing 56 during the operation of the compressor 16.
- the clearance 58 between the blades 52 of the rotor 50 and the casing 56 is too large, then the efficiency of the compressor 16 may be significantly reduced. For example, for certain compressors, a clearance 58 that is 10 mils larger than a desired clearance may result in roughly 1 MW loss in efficiency of the compressor 16. Furthermore, by providing a uniform clearance between the rotor and casing over the inner circumference of the casing may generally enable the rotary system to have more uniform performance (e.g., fewer fluctuations in power output).
- the casing 56 of the compressor 16 has at least one recess 60 that supports at least one insert 62 in accordance with aspects of the present technique.
- the recess 60 extends into the interior surface of the casing 56 in the radial direction 40 (i.e., having a radial depth 51 into the wall of the casing 56).
- the recess 60 may be formed by grinding or turning down a portion of the casing 56 after manufacturing.
- the recess 60 may be formed during the manufacturing of the casing 56 (e.g., as an element defined by the mold used to cast the casing 56).
- the recess 60 is an area of the casing in which a portion of the casing material (e.g., steel or other suitable metal or alloy) is absent or has been removed (e.g., via grinding or turning).
- the recess 60 may be in the form of a groove, a slot, a channel, or other similar recess 60.
- the recess 60 may be present in the casing 56 of the compressor 16 at portions where the various segments of the casing 56 meet (i.e., at or near casing segment joints).
- the recess 60 may have a particular shape (e.g., a V-shape, a rectangular shape, a rounded shape, or other suitable shape).
- an insert 62 is disposed within the recess 60.
- the insert 62 may slightly protrude radially 40 from the recess 60 into the clearance space 58.
- the insert 62 may extend between approximately 20 mm and 60 mm beyond the inner surface 53 of the casing 56.
- the illustrated insert 62 also includes at least two layers: a substrate layer 64 and an abradable surface coating 66.
- the substrate layer 64 of the insert 62 may be manufactured from the same material (e.g., metal or alloy) as the casing 56.
- the insert 62 and the casing 56 may both be manufactured from steel.
- the substrate layer 64 of the insert 62 may be manufactured from a different material (e.g., metal or alloy) than the casing 56.
- the substrate layer 64 of the insert 62 may be a different type of steel (e.g., higher carbon steel) than the casing 56.
- the material used for the substrate layer 64 of the insert 62 may be selected based on the thermal expansion properties of the material. That is, the substrate layer 64 of the insert 62 may have slightly different thermal expansion properties from the casing 56 such that the insert 62 and the casing 56 may not expand or contract at the same rate as they are heated and cooled (e.g., during operation of the compressor 16).
- the insert 62 is disposed within the recess 60 such that the abradable surface coating 66 is facing the blades 52 of the rotor 54.
- the abradable surface coating 66 may be any surface coating that may be preferentially removed upon contact with the blades 52 of the rotor 54, rather than remove material from the rotor blades 52 or the casing 56. That is, while the blades 52 of the rotor 54 are generally configured not to contact the casing 56, the aforementioned thermal expansion of the casing 56 during operation of the compressor may cause the blades 52 of the rotor 54 to temporarily contact the abradable surface coating 66 of the insert 62 (e.g., rather than the substrate 64 of the insert 62 or the casing 56).
- the abradable surface coating 66 may generally allow for tighter clearance 58 while protecting the tips of the blades 52. Additionally, the abradable surface coating 66 may generally be considered a self-adjusting coating as it may be slightly by the tips of the blades 52 until the desired clearance 58 is achieved. In certain embodiments, the abradable surface coatings 66 may be an alumina, silica, titania, chrome carbines, or other suitable abradable surface coating 66. In general, materials for the abradable surface coating 66 may be selected according to a relative hardness of the abradable surface coating 66 compared to the casing 56 and the blades 52 of the rotor 54.
- the abradable surface coating 66 may be manufactured from a material that is 10%, 20%, 50%, 75%, or 95% softer than the material used to manufacture the casing 56 and/or the blades 52. Additionally, as set forth below with respect to FIGS. 4 and 5 , the abradable surface coating 66 may either have either a uniform thickness or a variable thickness across the insert 62.
- FIG. 3 illustrates a cross-section of the embodiment of the compressor 16 illustrated in FIG. 2 taken within line 3-3 (i.e., without the rotor 54 and blades 52). Accordingly, FIG. 3 illustrates the location of the recesses 60 in the casing 56 of the compressor 16 relative to the locations of intermediate joints 70 and 72 (i.e., where the first segment 74 and the adjacent second segment 76 meet). While the illustrated embodiment of the casing 56 includes two 180° segments (e.g., segments 74 and 76), in other embodiments the casing 56 may include any number of segments (e.g., 3, 4, 5, 6 or more).
- the illustrated casing 56 includes recesses 60 that are generally deeper 59 near the joints 70 and 72 and become generally shallower 61 moving away from the joints in a circumferential direction 42. Additionally, the recesses 60 may occupy a portion of the casing 56 measured as an angle 71 from the point 73 at the center of the casing (e.g., the axis of rotation 38). For example, the illustrated angle 71 is approximately 60°. In certain embodiments, the angle 71 may be between approximately 10° and 60°, between approximately 20° and 50°, or between approximately 30° and 45°.
- each of the recesses 60 similarly are thicker in the portions that are disposed near the joints 70 and 72 and thinner in portions that are disposed away from the joints. Furthermore, in certain embodiments, a one-piece or integral insert 62 may be disposed in the each of the recesses 60, and each of these inserts 62 may occupy the entire recess 60 that extends circumferentially 38 into both segments 74 and 76 of the compressor casing 56.
- recesses 60 include a recess portion 63 and a recess portion 65 that are each loaded with an insert 62.
- each recess 60 of the illustrated casing 56 includes a first insert 62 (e.g., disposed within the recess portion 63 of the recess 60 in segment 74) and a second insert 62 (e.g., disposed within the recess portion 65 of the recess 60 in segment 76).
- the illustrated casing 56 of the compressor 16 is substantially round (i.e., circular). Furthermore, it should be appreciated that, as the casing 56 warms or cools during operation of the compressor 16, the portions of the segments 74 and 76 near the joints 70 and 72 may not expands or contract as much as the portions of the segments 74 and 76 away from the joints 70 and 72. That is, since the casing 56 may generally have more freedom to move near the joints 70 and 72, the casing 56 generally push outwardly 67 or pull inwardly 69 (e.g., center 73 of the casing 56), deforming at the joints 70 and 72 (e.g., shift out of roundness and/or become eccentric).
- the illustrated casing 56 has the recesses 60 with the inserts 62 disposed within. Accordingly, as the casing 56 begins to thermally expand, the recesses 60 and the inserts 62 enable the casing 56 of the compressor to thermally expand without becoming substantially eccentric. That is, the recesses 60 and the inserts 62 generally enable the clearance 58 between the blades 52 of the rotor 54 to remain substantially uniform throughout the operation of the compressor 16.
- the recesses 60 and inserts 62 may cooperate to provide a uniform clearance 58 (e.g., circumferentially 38 between the rotor blades 52 and the casing 56 and insert 62) of between 1 mm and 50 mm, between 5 mm and 30 mm, between 8 mm and 20 mm, or approximately 10 mm at the joints 70 and 72.
- a uniform clearance 58 e.g., circumferentially 38 between the rotor blades 52 and the casing 56 and insert 62
- a uniform clearance 58 e.g., circumferentially 38 between the rotor blades 52 and the casing 56 and insert 62
- FIG. 4 illustrates an enlarged view of the joint 70 of the casing embodiment illustrated in FIG. 3 . Accordingly, FIG. 4 illustrates the recess 60 in the segments 74 and 76 of the casing 56. Moreover, the illustrated recess 60 is substantially deeper 59 near the joint 70 and substantially shallower 61 away from the joint 70. Furthermore, the insert 62, including the substrate 64 and the abradable coating 66, is disposed within the illustrated recess 60. Like the illustrated recess 60, the insert 62 is substantially thicker 75 at the portion disposed near the joint 70 and substantially thinner 77 at the portion disposed away from the joint 70. In other embodiments, the recess 60 and the insert 62 may both have a substantially uniform radial 40 depth and thickness, respectively.
- the abradable coating 66 of the illustrated insert 62 is substantially thicker 79 near the joint 70 and substantially thinner 81 moving away from the joint 70 circumferentially 42. Accordingly, in certain embodiments, the recess 60, the insert 62, and/or the abradable coating 66 may generally be described as having a generally arcuate shape. In other embodiments, the abradable coating 66 may have a substantially uniform thickness over the length of the insert 62.
- FIG. 5 is a partial perspective view of one segment of the segmented stator of FIGS. 1-4 , illustrating a T-shaped joint 83 that couples the eccentricity control insert 62 to the recess 60. That is, FIG. 5 illustrates the insert 62 disposed within the recess 60 of segment 76 of the casing 56.
- the illustrated recess 60 includes the T-shaped joint 83 and, accordingly, the insert 62 is a T-shaped insert 62.
- the recess 60 and the insert 62 may have a dove-tail shape, a rounded shape, a "V" shape, a triangular shape, a semicircular shape, or other suitable shape.
- the T-shaped joint 83 includes ridge portions 85 that may generally serve to hold the insert 62 in place within the T-shaped joint 83.
- the illustrated T-shaped insert 62 includes a neck portion 89 and a mounting base portion 91 that extend in a lengthwise direction along the eccentricity control insert 62, and the mounting base portion 91 is wider than the neck portion 89 in a crosswise direction relative to the lengthwise direction.
- the abradable coating 66 of the insert 62 extends beyond the neck portions 85 such that, during operation, the tips blades 52 of the rotor 54 most proximate to the abradable coating 66 of the insert 62.
- the insert 62 may be introduced into the T-shaped joint 83 from the top portion 85 of the joint 83, and seated in a downward motion 87 such that the insert 62 is circumferentially loaded or mounted into the segment 76 of the casing 56.
- the illustrated insert 62 is substantially thicker 75 near the joint 70. That is, both the substrate 64 and the abradable coating 66 of the illustrated insert 62 are substantially thicker 75 near the joint 70 and gradually taper along the segment 76 (i.e., moving away from the joint 70 circumferentially 42), where the substrate 64 and the abradable coating 66 of the illustrated insert 62 are thinner 77. Accordingly, when the blades 52 of the rotor 54 are rotating during operation of the compressor 16, the groove 60 and the insert 62 may provide a uniform circumferential clearance 58 such that the compressor 16 may efficiently function.
- inventions include mitigating the eccentricity of stators in rotor/stator system (e.g., casings for compressors, gas turbines, steam turbines, pumps, or other rotary machines) in order to control the clearance between the rotor and the stator as the system expands and/or contracts during heating and/or cooling.
- rotor/stator system e.g., casings for compressors, gas turbines, steam turbines, pumps, or other rotary machines
- present embodiments enable the compressor or gas turbine to continue to properly and efficiently function, even as the casing expands and contracts during operation.
- present embodiments may reduce maintenance costs by reducing the likelihood of contact between the rotor blades in the casing and by providing an abradable coating that may be preferentially removed to preserve the integrity of the rotor blades and/or casing in case of contact. Furthermore, present embodiments enable the compressor or gas turbine to maintain efficiency during operation, limiting energy costs and waste.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/416,982 US20130236293A1 (en) | 2012-03-09 | 2012-03-09 | Systems and methods for an improved stator |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2636850A1 true EP2636850A1 (fr) | 2013-09-11 |
EP2636850B1 EP2636850B1 (fr) | 2015-05-13 |
Family
ID=47844185
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP20130158473 Not-in-force EP2636850B1 (fr) | 2012-03-09 | 2013-03-08 | Stator des turbines à gaz |
Country Status (5)
Country | Link |
---|---|
US (1) | US20130236293A1 (fr) |
EP (1) | EP2636850B1 (fr) |
JP (1) | JP2013185593A (fr) |
CN (1) | CN103306745A (fr) |
RU (1) | RU2013110038A (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2015043811A1 (fr) * | 2013-09-30 | 2015-04-02 | Siemens Aktiengesellschaft | Garniture abradable et dispositif d'étanchéité |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3015671B1 (fr) * | 2013-12-23 | 2020-03-20 | Safran Helicopter Engines | Ensemble pour turbomachine pour mesurer des vibrations subies par une pale en rotation |
JP2016113992A (ja) * | 2014-12-16 | 2016-06-23 | 三菱重工業株式会社 | 圧力容器およびタービン |
DE102015202070A1 (de) * | 2015-02-05 | 2016-08-25 | MTU Aero Engines AG | Gasturbinenbauteil |
US10900371B2 (en) | 2017-07-27 | 2021-01-26 | Rolls-Royce North American Technologies, Inc. | Abradable coatings for high-performance systems |
US10858950B2 (en) | 2017-07-27 | 2020-12-08 | Rolls-Royce North America Technologies, Inc. | Multilayer abradable coatings for high-performance systems |
US10808565B2 (en) * | 2018-05-22 | 2020-10-20 | Rolls-Royce Plc | Tapered abradable coatings |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2962256A (en) * | 1956-03-28 | 1960-11-29 | Napier & Son Ltd | Turbine blade shroud rings |
GB2139295A (en) * | 1983-05-05 | 1984-11-07 | Tuomo Kaivola | Thermal joint e.g. for a turbine |
US5593278A (en) * | 1982-12-31 | 1997-01-14 | Societe National D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. | Gas turbine engine rotor blading sealing device |
US20020119338A1 (en) * | 1999-06-29 | 2002-08-29 | Wayne Charles Hasz | Tubine engine component having wear coating and method for coating a turbine engine component |
EP2182175A2 (fr) * | 2008-10-30 | 2010-05-05 | General Electric Company | Structure de boîtier et procédé pour améliorer la reponse thermique d'une turbine pendant des modes operatoires transitoires et stables |
EP2392779A1 (fr) * | 2010-06-03 | 2011-12-07 | General Electric Company | Virole de compresseur de turbomachine |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4522559A (en) * | 1982-02-19 | 1985-06-11 | General Electric Company | Compressor casing |
-
2012
- 2012-03-09 US US13/416,982 patent/US20130236293A1/en not_active Abandoned
-
2013
- 2013-03-06 RU RU2013110038/06A patent/RU2013110038A/ru not_active Application Discontinuation
- 2013-03-06 JP JP2013043611A patent/JP2013185593A/ja active Pending
- 2013-03-08 CN CN2013100740124A patent/CN103306745A/zh active Pending
- 2013-03-08 EP EP20130158473 patent/EP2636850B1/fr not_active Not-in-force
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2962256A (en) * | 1956-03-28 | 1960-11-29 | Napier & Son Ltd | Turbine blade shroud rings |
US5593278A (en) * | 1982-12-31 | 1997-01-14 | Societe National D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. | Gas turbine engine rotor blading sealing device |
GB2139295A (en) * | 1983-05-05 | 1984-11-07 | Tuomo Kaivola | Thermal joint e.g. for a turbine |
US20020119338A1 (en) * | 1999-06-29 | 2002-08-29 | Wayne Charles Hasz | Tubine engine component having wear coating and method for coating a turbine engine component |
EP2182175A2 (fr) * | 2008-10-30 | 2010-05-05 | General Electric Company | Structure de boîtier et procédé pour améliorer la reponse thermique d'une turbine pendant des modes operatoires transitoires et stables |
EP2392779A1 (fr) * | 2010-06-03 | 2011-12-07 | General Electric Company | Virole de compresseur de turbomachine |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2015043811A1 (fr) * | 2013-09-30 | 2015-04-02 | Siemens Aktiengesellschaft | Garniture abradable et dispositif d'étanchéité |
Also Published As
Publication number | Publication date |
---|---|
CN103306745A (zh) | 2013-09-18 |
JP2013185593A (ja) | 2013-09-19 |
RU2013110038A (ru) | 2014-09-20 |
EP2636850B1 (fr) | 2015-05-13 |
US20130236293A1 (en) | 2013-09-12 |
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