EP2129875A2 - Turbomaschine mit active clearance control - Google Patents
Turbomaschine mit active clearance controlInfo
- Publication number
- EP2129875A2 EP2129875A2 EP08706764A EP08706764A EP2129875A2 EP 2129875 A2 EP2129875 A2 EP 2129875A2 EP 08706764 A EP08706764 A EP 08706764A EP 08706764 A EP08706764 A EP 08706764A EP 2129875 A2 EP2129875 A2 EP 2129875A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- shroud
- adjusting device
- gap
- turbomachine according
- rotation
- 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
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
- 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
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/20—Three-dimensional
- F05D2250/29—Three-dimensional machined; miscellaneous
- F05D2250/292—Three-dimensional machined; miscellaneous tapered
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/50—Kinematic linkage, i.e. transmission of position
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/501—Elasticity
Definitions
- the invention relates to a turbomachine, in particular a gas turbine, according to the preamble of claim 1 or 6 or 11.
- a turbomachine with a stator and a rotor wherein the rotor blades and the stator has a housing and vanes.
- the rotor-side blades form at least one blade ring, which is adjacent at a radially outer end to a radially inner housing wall of the housing, is surrounded by the same and defines a radial gap with the same.
- the radially inner housing wall of the housing is also referred to as a shroud and serves in particular as a carrier for an inlet lining.
- the gap between the shroud of the housing and the radially outer end of the or each blade ring to provide a so-called Active Clearance Control can be adjusted or adjusted by means of adjusting devices in its gap, so to automatically influence the gap and to ensure an optimal gap position over all operating conditions.
- the radially inner housing wall or the outer ring is segmented in the circumferential direction, wherein preferably each segment is assigned a separate actuating device.
- the adjusting devices are preferably designed as electro-mechanical actuators.
- the arrangement of the electro-mechanical actuators, which act on the segments of the radially inner housing wall and the shroud takes a relatively large amount of space, which increases the overall dimensions of the turbomachine.
- the present invention is based on the problem to provide a novel turbomachine with Active Clearance Control, which has smaller dimensions.
- the shroud ring is designed as a coupling ring.
- concentrically surrounded actuating device wherein opposing surfaces of the shroud and the adjusting device are contoured frustoconical, and wherein between the shroud and the adjusting device in the radial direction and in the circumferential direction with respect to the axial obliquely angebring, cylindrical rolling elements are positioned so that the adjusting device relative to the shroud is rotatable with simultaneous adjustment of the gap.
- this problem is solved by a turbomachine according to claim 6.
- the shroud is concentrically surrounded by a trained as a coupling ring adjusting device, wherein opposing surfaces of the shroud and the actuator are contoured cylindrical, wherein between the shroud and the actuator clamping body-like, non-cylindrical rolling elements are positioned, depending on their rotational position a different radial extent have, and wherein the adjusting device relative to the shroud with simultaneous adjustment of the gap is rotatable.
- this problem is solved by a turbomachine according to claim 11.
- the shroud of a trained as a coupling ring adjusting device is concentrically surrounded, with opposite surfaces of the shroud and the actuator are contoured such that one of the surfaces is cylindrical and the other of the surfaces ramped contoured, and wherein between the shroud and the actuator cylindrical rolling elements are positioned so that the adjusting device relative to the shroud with simultaneous adjustment of the gap is rotatable.
- the inventive concepts of an active clearance control on a turbomachine come with a relatively small space, so that only slightly increases the overall size of a turbomachine. Due to the relatively simple structural design, the turbomachine is also susceptible to wear. Furthermore, only small adjustment forces are required to rotate the ring-like adjusting device relative to the jacket ring for adjusting the gap. Another advantage is that the involved assemblies are mainly subjected to train and pressure, but no or only a small bending stress are exposed.
- Fig. 1 is a highly schematic detail of a turbomachine according to the invention according to a first aspect of the present invention
- 2 shows a highly schematic detail of a turbomachine according to the invention according to a second aspect of the present invention
- FIG. 3 shows a highly schematic detail of a turbomachine according to the invention according to a third aspect of the present invention.
- the present invention relates to a turbomachine, in particular a gas turbine, such as e.g. a gas turbine aircraft engine.
- a turbomachine in particular a gas turbine, such as e.g. a gas turbine aircraft engine.
- Such turbomachines have at least one compressor, at least one combustion chamber and at least one turbine, wherein both in the region of the or each compressor and in the region of the or each turbine, a stator and a rotor is present.
- the rotor of a compressor or a turbine comprises a plurality of rotating blades.
- the stator of a compressor or a turbine comprises a housing and a plurality of stationary vanes.
- the blades associated with the rotor rotate with respect to the fixed housing and fixed stator vanes, the vanes forming vane rings and the rotor blades forming rotor blades.
- a rotor blade ring is positioned between two guide vane rings arranged one behind the other in the direction of flow.
- Both in the region of the or each compressor and in the region of the or each turbine of a turbomachine is between a radially outer end of a blade ring and a radially inner housing wall of the housing, which serves as a shroud is designated, a gap formed, which must be as small as possible to optimize the efficiency of the turbomachine.
- the present invention now relates to such details of a turbomachine, by means of which the gap between the radially outer end of a blade ring and the radially inner housing wall or the outer ring of a housing in the sense of an Active Clearance Control can be automatically influenced or changed.
- the invention is preferably used in the region of a compressor of a turbomachine.
- the invention is not limited to use in the area of the compressor, but the invention can also be used in the area of a turbine of a turbomachine.
- Fig. 1 shows a highly schematic section of a turbomachine according to the invention according to a first aspect of the present invention.
- FIG. 1 shows a radially inner housing wall or a shroud 10 of a stator of a compressor of a gas turbine, wherein the shroud 10 encloses a non-illustrated blade ring. Between the shroud 10 and a radially outer end of the blade ring, not shown, a likewise not shown gap is formed.
- the shroud 10 is concentrically surrounded by a trained as a coupling ring adjusting device 11. 1 opposite surfaces 12, 13 of the outer ring 10 and adjusting device 11 are frustoconical contoured, wherein between the opposing surfaces 12 and 13 of the shroud 10 and actuator 11 and thus between the shroud 10 and actuator 11 formed as a cylindrical rollers rolling elements 14 are arranged are, which are inclined relative to the axial direction of the shroud 10 in the radial direction and in the circumferential direction. Due to the fact that between the shroud 10 and the adjusting device 11, which surrounds the shroud 10 concentrically, the rolling elements 14 are arranged, the adjusting device 11 can be rotated relative to the shroud 10.
- rolling elements 14 are preferably formed as so-called cage-guided rollers.
- the gap of the gap based on an initial dimension can be reduced in a first direction of rotation of the ring-like adjusting device 11, in a second direction of rotation of the adjusting device 11, the gap is compared to the réelleheld enlarged.
- a mechanism which consists essentially of two concentric rings, namely a first one Ring, which is formed by the shroud 10, and a second ring, which is formed by the adjusting device 11. Between these two rings, ie between the shroud 10 and the adjusting device 11, rolling elements 14 designed as rollers are preferably arranged, which allow the adjusting device 11 to rotate relative to the shroud 10.
- rolling elements 14 are relative to the axial extension of the housing wall 10 and thus is inclined relative to the axial extent of the turbomachine in the circumferential direction and in the radial direction, wherein the opposing surfaces 12, 13 of the outer ring 10 and adjusting device 11, between which the rolling elements 14 are arranged frustoconical contoured.
- the rotation of the adjusting device 11 relative to the shroud 10 further causes an axial displacement of the adjusting device 11 relative to the shroud 10.
- the adjusting device 11 is screwed onto the shroud 10, so to speak.
- the executed in a relatively thick wall thickness adjusting device 11 deforms the executed in a relatively thin wall thickness shroud 10 in the sense of elastic deformation, so adjusted by turning the actuator 11 relative to the shroud 10, the diameter of the shroud 10 and thus the gap between the shroud and the blade ring can be adjusted.
- FIG. 2 shows a highly schematic section of a turbomachine according to the invention according to a second aspect of the present invention.
- FIG. 2 again shows a radially inner housing wall or a shroud 17 of a stator of a compressor of a gas turbine, the shroud 17 enclosing a rotor blade ring (not shown). Between the shroud 17 and the radially outer end of the rotor blade ring, not shown, in turn, a non-illustrated gap is formed.
- the shroud 17 is concentrically surrounded by a trained as a coupling ring adjusting device 18.
- opposite surfaces 19 and 20 of the outer ring 17 and the adjusting device 18 are cylindrically contoured, non-cylindrical, clamping body-like rolling elements 21 being arranged between the opposing surfaces 19, 20.
- the clamping body-like rolling elements 21 are guided in cages 22, 23 under prestress via a spring element 24.
- the adjusting device 18 is rotated relative to the shroud 17, wherein during the rotation of the adjusting device 18 relative to the shroud 17 and the rolling elements 21 are rotated, the rolling elements 21 depending on their rotational position have a different radial extent.
- the shroud 17 is deformed by reducing the gap between the shroud 17 and the radially outer ends of the blades, not shown.
- the adjusting device 18 is rotated relative to the shroud 17 such that, as a result of this rotation, the radial extent of the rolling elements 21 decreases.
- FIG. 3 A schematic section of a turbomachine according to the invention according to a third aspect of the present invention, Fig. 3, wherein also in Fig. 3, a jacket ring 25 of a stator of a compressor of a gas turbine is shown, which encloses a non-illustrated blade ring and with the non-illustrated illustrated blade ring limits a gap, also not shown. Also in the embodiment of Fig. 3, the shroud 25 is concentrically surrounded by a trained as a coupling ring adjusting device 26. Opposing surfaces 27 and 28 of shroud 27 and actuator 26 are contoured in the embodiment of FIG. 3 such that the surface 28 of the actuator 26 is cylindrical and the surface 27 of the shroud 25 is contoured in a ridge shape.
- a plurality of ramps 30 are formed on the surface 27 of the shroud 25, on which roll between the opposing surfaces 27 and 28 of the shroud 25 and actuator 26, cylindrical rolling elements 29 roll.
- the surface 27 of the jacket 25 may be cylindrical and the surface 28 of the actuator 26 may be contoured ramped.
- the rolling elements 29 roll on the formed in the area of the surface 27 ramps 30, at the same time the shroud 27 and thus the gap between the shroud 27 and the non-illustrated blade ring can be changed and thus adjusted ,
- the gap is reduced in relation to an initial dimension; in a second direction of rotation of the adjusting device 26, the gap dimension of the gap relative to the initial dimension can be increased.
- the adjusting device 18 or 20 in a relatively thick wall thickness and the shroud 17 and 25 in a relatively thin wall thickness.
- the shroud 17 or 25 is subject to an elastic deformation as a result of the rotation of the actuating device 18 or 26.
- the inventive mechanism for providing an active clearance control on a turbomachine is characterized by a compact design with a low overall height. There are only small adjustment forces and no holding forces required. Components are mainly loaded on train and pressure, but are exposed to little or no bending load.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Radiation-Therapy Devices (AREA)
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102007003028A DE102007003028A1 (de) | 2007-01-20 | 2007-01-20 | Turbomaschine |
PCT/DE2008/000067 WO2008086782A2 (de) | 2007-01-20 | 2008-01-16 | Turbomaschine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2129875A2 true EP2129875A2 (de) | 2009-12-09 |
EP2129875B1 EP2129875B1 (de) | 2011-03-09 |
Family
ID=39530809
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08706764A Not-in-force EP2129875B1 (de) | 2007-01-20 | 2008-01-16 | Turbomaschine mit active clearance control |
Country Status (7)
Country | Link |
---|---|
US (1) | US8376691B2 (de) |
EP (1) | EP2129875B1 (de) |
AT (1) | ATE501340T1 (de) |
CA (1) | CA2676012A1 (de) |
DE (2) | DE102007003028A1 (de) |
ES (1) | ES2358165T3 (de) |
WO (1) | WO2008086782A2 (de) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20070162152A1 (en) * | 2005-03-31 | 2007-07-12 | Massachusetts Institute Of Technology | Artificial joints using agonist-antagonist actuators |
DE102008042262B4 (de) | 2008-09-22 | 2010-05-27 | Bundesdruckerei Gmbh | Verfahren zur Speicherung von Daten, Computerprogrammprodukt, ID-Token und Computersystem |
DE102008042582A1 (de) | 2008-10-02 | 2010-04-08 | Bundesdruckerei Gmbh | Telekommunikationsverfahren, Computerprogrammprodukt und Computersystem |
EP2233701A1 (de) | 2009-03-26 | 2010-09-29 | Siemens Aktiengesellschaft | Axialturbomaschine mit axial verschiebbarem Leitschaufelträger |
US9784117B2 (en) | 2015-06-04 | 2017-10-10 | United Technologies Corporation | Turbine engine tip clearance control system with rocker arms |
US9752450B2 (en) * | 2015-06-04 | 2017-09-05 | United Technologies Corporation | Turbine engine tip clearance control system with later translatable slide block |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3227418A (en) * | 1963-11-04 | 1966-01-04 | Gen Electric | Variable clearance seal |
US4127357A (en) * | 1977-06-24 | 1978-11-28 | General Electric Company | Variable shroud for a turbomachine |
GB2416194B (en) * | 2004-07-15 | 2006-08-16 | Rolls Royce Plc | A spacer arrangement |
DE102004037955A1 (de) | 2004-08-05 | 2006-03-16 | Mtu Aero Engines Gmbh | Turbomaschine, insbesondere Gasturbine |
EP1655455A1 (de) * | 2004-11-05 | 2006-05-10 | Siemens Aktiengesellschaft | Strömungsmaschine mit einem verstellbaren Leitschaufelträger zur Radialspalteinstellung |
-
2007
- 2007-01-20 DE DE102007003028A patent/DE102007003028A1/de not_active Withdrawn
-
2008
- 2008-01-16 CA CA002676012A patent/CA2676012A1/en not_active Abandoned
- 2008-01-16 ES ES08706764T patent/ES2358165T3/es active Active
- 2008-01-16 WO PCT/DE2008/000067 patent/WO2008086782A2/de active Application Filing
- 2008-01-16 DE DE502008002810T patent/DE502008002810D1/de active Active
- 2008-01-16 US US12/523,656 patent/US8376691B2/en not_active Expired - Fee Related
- 2008-01-16 EP EP08706764A patent/EP2129875B1/de not_active Not-in-force
- 2008-01-16 AT AT08706764T patent/ATE501340T1/de active
Non-Patent Citations (1)
Title |
---|
See references of WO2008086782A3 * |
Also Published As
Publication number | Publication date |
---|---|
WO2008086782A2 (de) | 2008-07-24 |
WO2008086782A3 (de) | 2009-11-19 |
US20100054921A1 (en) | 2010-03-04 |
DE502008002810D1 (en) | 2011-04-21 |
US8376691B2 (en) | 2013-02-19 |
DE102007003028A1 (de) | 2008-07-24 |
EP2129875B1 (de) | 2011-03-09 |
ES2358165T3 (es) | 2011-05-06 |
ATE501340T1 (de) | 2011-03-15 |
CA2676012A1 (en) | 2008-07-24 |
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