EP2386726A1 - Section de paroi de canal pour un canal d'écoulement annulaire d'une turbomachine axiale dotée d'un réglage du jeu en bout d'aube, compresseur axial et turbine à gaz associés - Google Patents

Section de paroi de canal pour un canal d'écoulement annulaire d'une turbomachine axiale dotée d'un réglage du jeu en bout d'aube, compresseur axial et turbine à gaz associés Download PDF

Info

Publication number: EP2386726A1
Authority: EP; European Patent Office
Prior art keywords: guide ring; wall section; channel wall; ring; axial
Prior art date: 2010-05-12
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

Application number

EP10005053A

Other languages

German (de)

English (en)

Other versions

EP2386726B1 (fr

Inventor

Richard Graefe

Carsten Kaufmann

Rafael Labish

Marco Link

Oliver Dr. Schneider

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

Siemens Corp

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.)

2010-05-12

Filing date

2010-05-12

Publication date

2011-11-16

2010-05-12 Application filed by Siemens AG, Siemens Corp filed Critical Siemens AG

2010-05-12 Priority to EP10005053A priority Critical patent/EP2386726B1/fr

2011-05-10 Priority to US13/104,186 priority patent/US8721270B2/en

2011-05-11 Priority to JP2011106143A priority patent/JP5844068B2/ja

2011-05-12 Priority to CN201110122307.5A priority patent/CN102242644B/zh

2011-11-16 Publication of EP2386726A1 publication Critical patent/EP2386726A1/fr

2012-10-31 Application granted granted Critical

2012-10-31 Publication of EP2386726B1 publication Critical patent/EP2386726B1/fr

Status Not-in-force legal-status Critical Current

2030-05-12 Anticipated expiration legal-status Critical

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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
- 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

Definitions

the invention relates to a channel wall portion of an annular flow channel of an axial turbomachine with radial gap adjustment.
flow channels are widely known.
the US 5,203,673 Such a device for regulating and adjusting radial gaps between the tips of the blades and the guide ring opposite thereto, which is part of the channel wall. It is provided that in the conical flow channel of the guide ring for adjusting radial gaps is axially displaceable.
three hydraulic cylinders are screwed in the guide vane support distributed over the circumference, the piston can move parallel to the machine axis of the turbine.
the conical gap between the flow path limiting wall surface of the guide ring and the correspondingly inclined tips of the blades can be adjusted by means of the axial displacement, the gap or the radial distance between the wall surface and blade tips.
the provision is made by means of coil springs, which move the guide ring back to its original position.
the use of a radial gap measuring system is provided with which the radial gap can be detected at one point.
the guide ring is then positioned axially in such a way that the smallest possible gap is achieved while avoiding the blade tip rubbing against the wall surface.
the disadvantage is the use of multiple hydraulic cylinders, since some of them may fail.
the object of the invention is to provide a compact duct wall portion for an annular flow channel of an axial turbomachine, with which a comparatively simple and reliable radial gap adjustment is possible without tilting of the guide ring takes place in case of failure of one of the hydraulic cylinder.
the guide ring which is arranged in a circumferential groove, has a first toothing on the front side, which rests against a second toothing arranged on a side wall of the circumferential groove, wherein it is additionally rotatable in the circumferential direction for the axial displacement of the displaceable guide ring.
the invention is based on the finding that the axial position of the guide ring is comparatively easily defined adjustable, when two mutually corresponding teeth always abut each other, of which a toothing is fixed and the other teeth relative to a toothing is slightly rotated, so that due to To the direction of displacement inclined tooth contact surfaces rotation of the teeth simultaneously causes or enforces their axial displacement.
the first toothing is intended to represent the rotatable toothing, which protrudes on the guide ring on the face side, ie from a plane perpendicular to the machine axis of the axial turbomachine.
the second toothing is fixed and arranged on the first toothing opposite side wall of the circumferential groove.
a plurality of uniformly distributed teeth over the circumference are provided, which means that at correspondingly many points the force is applied to adjust the guide ring, so that tilting of the guide ring can be safely avoided.
This also allows a distributed over the circumference uniform force application. Consequently, a local failure of the force introduction at only one point of the circumference can not occur. This results in a particularly reliable adjustability of the radial gaps, which are present between the flow path bounding inner wall surface of the guide ring and the tips of the passing below blades of the blades of the axial turbomachine.
the guide ring is by means of a spring element or a plurality of spring elements which are distributed over the circumference of the circumferential groove, always biased to the second toothing. An unwanted gap formation between the two gears can thus be safely avoided. This always leads to a clear axial position of the guide ring, which entails a clear gap.
spring elements are particularly disc springs.
the guide ring has an outwardly directed lateral surface with at least one outer toothing, in the circumferentially distributed over the circumference of the channel wall portion, engage in these rotatably mounted gears, wherein an all gears encompassing collar is provided, the internal teeth with the gears engaged is.
the preferably uniformly distributed over the circumference gears can accordingly many positions take place the introduction of force to the rotation of the guide ring, which means that the external teeth, the gears and the internal teeth can be made relatively small.
This construction is space-saving and, moreover, inexpensive to produce.
Both the external toothing and the internal toothing need not be designed as an endless peripheral toothing on the adjusting ring or on the guide ring, since only a short Vermosweg of the guide ring for adjusting the radial gaps is required.
the outer teeth arranged on the outer lateral surface of the guide ring and / or the inner teeth arranged on the adjusting ring are provided only at those circumferential positions at which toothed wheels are also provided in the channel wall section.
the force is introduced into the adjusting ring preferably via hydraulically or electrically actuated, engaging it push rods, as they are already known from the prior art.
Such drive devices are also used for the adjustment of rotatable inlet guide vanes of axial compressors. They usually have only a single drive unit.
the flow channel may have two or more relevant axially and circumferentially movable guide rings which are jointly driven either by a respective adjusting ring or by a collar. If two guide rings of the one adjusting ring are jointly driven, a synchronous adjustment of the radial gaps of two blade rings can be done.
an abrasion layer or a honeycomb-shaped layer is preferably provided on the inwardly directed wall surface of the guide ring.
a simple mountability of the required for the rotation of the guide ring gears and collars is possible if an externally or internally arranged receptacle in the channel wall portion is provided for each gear, in which a shaft or hub of the gear is rotatable or storable. Since the outer ring surrounds all the gears, their shaft or hubs need not be particularly secured in the appropriate recordings. Consequently, the shafts or hubs can only be inserted into the receptacles without the need for further constructive elements for secure positioning. However, the use of such elements is not excluded.
the guide ring, the channel wall section and / or the adjusting ring or the adjusting rings are each in at least two segments, i. Guide ring segments, wall section segments or adjusting ring segments, divisible, which allows the half assembly of the construction.
the channel wall portion is used in an axial compressor of an axially flowed gas turbine.
the use of the proposed invention is of particular interest in particular when the radial gaps present in the turbine unit of the gas turbine can be adjusted by an axial displacement of the rotor. Since the flow channel of the turbine unit and the flow channel of the compressor of the gas turbine in principle have opposite conical inclinations, the displacement of the rotor in the turbine unit leads to a radial gap minimization and in the compressor to an opening of the radial column. With the proposed channel wall section, in particular, the enlargement of the compressor radial gaps described by the aforementioned effect can be compensated for and possibly overcompensated, which, despite the rotor displacement, improves the compressor efficiency and thus the efficiency of the gas turbine leads.
the proposed channel wall portion is particularly suitable for compressors, since they are often operated in a temperature range, which allows the use of the proposed construction particularly simple.
the single FIGURE shows a longitudinal section of a section of an annular flow channel 10.
the annular flow channel 10 extends concentrically along a machine axis 12 of the axial flow-through turbomachine.
the turbomachine shown here is designed as a compressor of a gas turbine.
the flow channel 10 comprises a wall section 14, which represents the radially outer boundary of the flow path. Radially inside the flow path is limited either by an inner wall 16 or by the lateral surface of the rotor 18.
blades 20 are provided in rings. Between the two illustrated blade rings is a vane ring with a number of distributed over the circumference vanes 22, which are each held on the channel wall portion 14 by means of a hammer-shaped attachment.
Upstream of the FIG. 1 From left to right through flow channel 10 of the compressor is made of a plurality of segments existing guide ring 26 in an endless circumferential wall portion 14 circumferential groove 24.
the guide ring 26 is located at the axial position of in FIG. 1 Blade 20 shown on the left.
the guide ring 26 has an inwardly directed wall surface 28.
the wall surface 28 limits the flow path and is the tips 30th the blades 28 under gap formation 32 opposite.
the converging in this section wall surface 28 is therefore inclined relative to the machine axis 12 so that it is conical.
each receptacle 34 forms a pocket for a gear 38.
the gear 38 has a shaft or hub 40 which lies in the receptacle 34.
the gear 38 extends through the passage 36 and can engage in the arranged on the outer surface of the guide ring 26 outer teeth 35. All gears 38 are surrounded by a common adjusting ring 42, the internal teeth 44 with all gears 38 is engaged.
the outer teeth 35 has an axial width which is substantially greater than the axial width of the gear 38. This is necessary so that the guide ring 26 is always in spite of its displacement in the axial direction with the gears 38 in engagement.
the guide ring 26 is arranged in the endless circumferential groove 24.
a first toothing 50 is attached to the front side of the guide ring 26 by means of only schematically illustrated screws 48.
a second toothing 46 is attached analogously.
the first toothing 50 and the second toothing 46 are in a toothing plane 52 to each other.
the toothing plane 52 is formed like a sawtooth. It can also be designed in the manner of a Hirth toothing, which supports the centering of the guide ring 26. However, the toothing plane 52 is not shown in longitudinal section, but rotated by 90 ° to - in the manner of a settlement. Both teeth 46, 50 thus extend in the circumferential direction and not - as shown - in the radial direction.
a push rod 45 is coupled on the adjusting ring 42.
retaining elements 47 provided with a Collars surround the collar 42.
the displacement of the guide ring 26 in the axial direction is effected by a rotation of the adjusting ring 42.
the rotation of the adjusting ring 42 is converted into a rotation of the gears 38, which transmit their rotation to the guide ring 26.
the adjacent teeth 46, 50 force due to their relative movement to each other then a displacement of the guide ring 26 in the axial direction, in FIG. 1 to the left. This reduces the conical radial gaps 32.
an abrasive layer 56 is still provided on the wall surface 28 of the guide ring 26, which prevents damage in the case of a brushing of the blade tips 30 on the guide ring 26.
the holding elements 47 are adapted accordingly.
the adjusting ring 42 is then designed rather as a drum.
the adjustment of the size of the radial gaps between the wall surface 28 of the guide ring 26 and the opposite ends 30 of the blades 20 can already be performed during startup or during operation of the turbomachine or the gas turbine.
the radial gap adjustment can also take place as a function of a measured, actual radial gap.
gears 38 and the teeth 46, 50 may possibly be dispensed with lubricant, which is easy to maintain. Possibly. the sliding surfaces of the teeth 46, 50 are coated with polytetrafluoroethylene (PTFE). This allows a low-loss relative movement of the two gears 46, 50th
the invention provides a channel wall portion 14 of an annular flow channel 10 of an axial turbomachine which provides a particular simple, compact mechanism for adjusting radial gaps 32 between the inner wall surface 28 of a guide ring 26 and the blade edge 30 opposite this wall surface 28.
the guide ring 26 has frontally a first toothing 50 which rests on a on the side wall 27 of the guide ring 26 receiving circumferential groove 24 arranged second toothing 46, wherein the axial displacement of the displaceable guide ring 26 thereof is rotatable in the circumferential direction.

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Engineering & Computer Science (AREA)
Mechanical Engineering (AREA)
General Engineering & Computer Science (AREA)
Structures Of Non-Positive Displacement Pumps (AREA)

EP10005053A 2010-05-12 2010-05-12 Section de paroi de canal pour un canal d'écoulement annulaire d'une turbomachine axiale dotée d'un réglage du jeu en bout d'aube, compresseur axial et turbine à gaz associés Not-in-force EP2386726B1 (fr)

Priority Applications (4)

Application Number	Priority Date	Filing Date	Title
EP10005053A EP2386726B1 (fr)	2010-05-12	2010-05-12	Section de paroi de canal pour un canal d'écoulement annulaire d'une turbomachine axiale dotée d'un réglage du jeu en bout d'aube, compresseur axial et turbine à gaz associés
US13/104,186 US8721270B2 (en)	2010-05-12	2011-05-10	Passage wall section for an annular flow passage of an axial turbomachine with radial gap adjustment
JP2011106143A JP5844068B2 (ja)	2010-05-12	2011-05-11	軸流式ターボ機械の環状流路のための、径方向間隙を調整可能な流路壁
CN201110122307.5A CN102242644B (zh)	2010-05-12	2011-05-12	用于轴流式涡轮机的环形的流动通道的具有径向缝隙调节功能的通道壁段

Applications Claiming Priority (1)

Application Number	Priority Date	Filing Date	Title
EP10005053A EP2386726B1 (fr)	2010-05-12	2010-05-12	Section de paroi de canal pour un canal d'écoulement annulaire d'une turbomachine axiale dotée d'un réglage du jeu en bout d'aube, compresseur axial et turbine à gaz associés

Publications (2)

Publication Number	Publication Date
EP2386726A1 true EP2386726A1 (fr)	2011-11-16
EP2386726B1 EP2386726B1 (fr)	2012-10-31

Family

ID=42634902

Family Applications (1)

Application Number	Title	Priority Date	Filing Date
EP10005053A Not-in-force EP2386726B1 (fr)	2010-05-12	2010-05-12	Section de paroi de canal pour un canal d'écoulement annulaire d'une turbomachine axiale dotée d'un réglage du jeu en bout d'aube, compresseur axial et turbine à gaz associés

Country Status (4)

Country	Link
US (1)	US8721270B2 (fr)
EP (1)	EP2386726B1 (fr)
JP (1)	JP5844068B2 (fr)
CN (1)	CN102242644B (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US9062554B2 (en) *	2012-01-03	2015-06-23	General Electric Company	Gas turbine nozzle with a flow groove
EP2623717A1 (fr) *	2012-02-02	2013-08-07	Siemens Aktiengesellschaft	Couronne d'aube pour une turbomachine axiale et procédé d'ajustement de la capacité de débit massique de la couronne d'aube
US9228447B2 (en)	2012-02-14	2016-01-05	United Technologies Corporation	Adjustable blade outer air seal apparatus
WO2017072843A1 (fr) *	2015-10-27	2017-05-04	三菱重工業株式会社	Machine rotative
US10704560B2 (en)	2018-06-13	2020-07-07	Rolls-Royce Corporation	Passive clearance control for a centrifugal impeller shroud
US11459912B2 (en)	2018-07-13	2022-10-04	Mitsubishi Heavy Industries, Ltd.	Flow guide, steam turbine, inside member, and method for manufacturing flow guide
KR102316629B1 (ko)	2020-06-23	2021-10-25	두산중공업 주식회사	터빈 블레이드 팁 간극 제어장치 및 이를 포함하는 가스 터빈
CN113107855B (zh) *	2021-04-25	2022-12-30	济宁安泰矿山设备制造有限公司	一种径向间隙调节结构、调节方法及抢险排水泵
US12345162B2 (en)	2023-11-17	2025-07-01	Rolls-Royce Corporation	Adjustable position impeller shroud for centrifugal compressors
US12345163B2 (en)	2023-11-17	2025-07-01	Rolls-Royce Corporation	Travel stop for a tip clearance control system

Citations (2)

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Publication number	Priority date	Publication date	Assignee	Title
US3227418A (en) *	1963-11-04	1966-01-04	Gen Electric	Variable clearance seal
US5203673A (en)	1992-01-21	1993-04-20	Westinghouse Electric Corp.	Tip clearance control apparatus for a turbo-machine blade

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DE1178253B (de) *	1962-03-03	1964-09-17	Maschf Augsburg Nuernberg Ag	Axial-durchstroemte Kreiselradmaschine mit einstellbarem Deckband
US4127357A (en) *	1977-06-24	1978-11-28	General Electric Company	Variable shroud for a turbomachine
GB2042646B (en) *	1979-02-20	1982-09-22	Rolls Royce	Rotor blade tip clearance control for gas turbine engine
JPS59135395U (ja) *	1983-03-02	1984-09-10	株式会社日立製作所	軸流形流体機械のチツプ空隙調整装置
DE10060740A1 (de) *	2000-12-07	2002-06-13	Alstom Switzerland Ltd	Vorrichtung zur Spaltmasseinstellung für eine Strömungsmaschine
EP1243756A1 (fr) *	2001-03-23	2002-09-25	Siemens Aktiengesellschaft	Turbine
CN1692179B (zh) *	2002-10-09	2011-07-13	石川岛播磨重工业株式会社	回转体及其涂覆方法
US7686569B2 (en) *	2006-12-04	2010-03-30	Siemens Energy, Inc.	Blade clearance system for a turbine engine

2010
- 2010-05-12 EP EP10005053A patent/EP2386726B1/fr not_active Not-in-force
2011
- 2011-05-10 US US13/104,186 patent/US8721270B2/en not_active Expired - Fee Related
- 2011-05-11 JP JP2011106143A patent/JP5844068B2/ja not_active Expired - Fee Related
- 2011-05-12 CN CN201110122307.5A patent/CN102242644B/zh not_active Expired - Fee Related

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number	Priority date	Publication date	Assignee	Title
US3227418A (en) *	1963-11-04	1966-01-04	Gen Electric	Variable clearance seal
US5203673A (en)	1992-01-21	1993-04-20	Westinghouse Electric Corp.	Tip clearance control apparatus for a turbo-machine blade

Also Published As

Publication number	Publication date
US8721270B2 (en)	2014-05-13
US20110280712A1 (en)	2011-11-17
JP2011236911A (ja)	2011-11-24
CN102242644B (zh)	2015-07-22
JP5844068B2 (ja)	2016-01-13
CN102242644A (zh)	2011-11-16
EP2386726B1 (fr)	2012-10-31

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