EP2392780A2 - Dispositif d'étanchéité et réglage du jeu des extrémités d'aubes - Google Patents

Dispositif d'étanchéité et réglage du jeu des extrémités d'aubes Download PDF

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Publication number
EP2392780A2
EP2392780A2 EP11168277A EP11168277A EP2392780A2 EP 2392780 A2 EP2392780 A2 EP 2392780A2 EP 11168277 A EP11168277 A EP 11168277A EP 11168277 A EP11168277 A EP 11168277A EP 2392780 A2 EP2392780 A2 EP 2392780A2
Authority
EP
European Patent Office
Prior art keywords
housing
flex beam
set forth
seal
flex
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.)
Withdrawn
Application number
EP11168277A
Other languages
German (de)
English (en)
Other versions
EP2392780A3 (fr
Inventor
Joel H. Wagner
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.)
RTX Corp
Original Assignee
United Technologies 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.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP2392780A2 publication Critical patent/EP2392780A2/fr
Publication of EP2392780A3 publication Critical patent/EP2392780A3/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • 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
    • F05D2260/00—Function
    • F05D2260/40—Transmission of power
    • F05D2260/406—Transmission of power through hydraulic systems

Definitions

  • Gas turbine engines typically include a compressor delivering compressed gas into a combustion chamber.
  • the compressed air is mixed with fuel and combusted in the combustion chamber.
  • the hot products of combustion pass downstream over turbine rotors, driving the rotors to create power.
  • blade outer air seals are typically placed radially outwardly of the radially outermost tip of the airfoil on turbine blades associated with the rotors.
  • the clearance between the blade outer air seal and the tip of the airfoil is desirably tightly controlled.
  • various factors raise challenges with maintaining this clearance.
  • various ways for adjusting this clearance such as the use of thermal control methods have been proposed.
  • a turbine section in a described construction, includes a housing and a blade outer air seal to be mounted on the housing.
  • a flexible beam member enables mounting of the blade outer air seal onto the housing, with the flex beam being supported on the housing, but free to move relative to the housing.
  • a pressure air chamber is formed on an opposed side of the flex beam from the blade outer air seal.
  • a source of pressurized air is delivered into the chamber to cause the flex beam to move the blade outer air seal toward and away from a central axis of the housing.
  • FIG. 1 A portion of a turbine section 20 of a gas turbine engine is illustrated in Figure 1 .
  • An air inlet 22 communicates with a valve 24.
  • the valve 24 is controlled by a control 26.
  • the control 26 controls the valve 24 to supply high pressure air such as from a compressor 28 which is part of the gas turbine engine through the valve 24, the air inlet 22, and into a pressure chamber 30.
  • the pressure chamber 30 is defined by a housing 31 having static mounts 32 holding a flex beam 34.
  • the flex beam 34 is formed of an appropriate material and is formed to be thin enough such that it can flex radially inwardly and outwardly.
  • the housing 31 can be formed by plural housing portions.
  • the flex beam should be designed for repeated flexure operation and formed of an appropriate material that is able to retain reliable spring deflection characteristics in a high temperature environment, and have consistent spring deflection characteristics over a wide temperature range.
  • the flex beam is relatively thin. As one example only, it may be on the order of 0.030 in - 0.050 in (0.762 mm - 1.27 mm). The thickness of the beam is shown exaggerated in the Figures, as the beam would be so thin as to be hard to see if illustrated proportionally. In addition, as is clear from the Figures, the beam may have a relatively thinner portion aligned with the space 300, which will be described below.
  • the flex beam 34 is not fixed within channels defined by the static mounts 32, but rather supported there. Seals 36 are placed in a slot 56 in the flex beam to provide a seal at the location. Wire seals are shown although other seal configurations could be used. Blade outer air seal mounts 44 and 48 on the flex beam secure hooks 50 on a blade outer air seal 42. The blade outer air seal 42 is removable from the flex beam 34 for service and repair. The blade outer air seal 42 is shown schematically. The blade outer air seal has an inner peripheral surface closely spaced from an outer tip of an airfoil of a rotor blade 40. A vane 38 is positioned upstream of the blade 40.
  • pressurized air may be delivered into the pressure chamber 30.
  • the opposed side of the flex beam from the pressure chamber 30 is exposed to lower pressure air.
  • the delivery of the high pressure air into pressure chamber 30 will flex the flex beam 34 downwardly, such that the blade outer air seal 42 approaches the blade 40, and the clearance is reduced.
  • applying a lower pressure air to the opposed side will flex the beam upwardly, such that the blade outer air seal 42 is moved away from the blade 40, and the clearance is increased.
  • the control 26 can take in information about a variety of engine characteristics, and determine the amount of pressure to be delivered into the pressure chamber 30 to achieve a desired clearance. These aspects of the invention are generally as known. That is, the amount of clearance desirable would be as known, but the way of achieving the desired clearance is inventive here.
  • Known electronic controls can be utilized.
  • other type controllers such as, for example, a pneumatic controller, may be utilized.
  • FIG 2 shows that the flex beams 34 are positioned adjacent to each other in a circumferential direction about a center axis X (see Figure 1 ) of rotation of the blade 40.
  • Each flex beam 34 has one circumferential edge 52 and an opposed circumferential edge 150.
  • the seal 54 is received in a slot 56 at the edge 150.
  • Figure 3 shows the flex beam 34 having the slot 56 which includes side slot portions 58 and 60.
  • the seal 54 may be c-shaped and positioned within the slot 56, 58,60.
  • Figure 4 shows another embodiment 100 having a blade 146, vane 148, and blade outer air seal 140.
  • the blade outer air seal 140 has hooks 142 and 144 associated with blade outer air seal mounts 136 and 138 defining channels in a flex beam 134.
  • One edge 150 of the flex beam is received on a static mount 152 of a housing 110. As can be appreciated, there is clearance at this interface such that the flex beam can move to the right or left in this Figure.
  • the opposed end 156 of the flex beam has a surface 161 in contact with an inner surface of the housing 110.
  • the opposed end 156 is fixed to move with a portion 158, which is in contact with a seal 160 in a housing channel 162.
  • This two-bar connection guides the flex beam 134 for movement such that it maintains the blade outer air seal 140 in a proper orientation relative to the blade 146 even when it flexes.
  • FIG. 3 there is a space 300 formed between the flex beams 34 or 134 and their associated blade outer air seals 42 or 140.
  • the space 300 facilitates the radially inward flexing of the flex beam 34, 134, which might otherwise be less pronounced if there was contact between the blade outer air seal 42, 140 and the flex beam 34,134 at that location.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP11168277.9A 2010-06-01 2011-05-31 Dispositif d'étanchéité et réglage du jeu des extrémités d'aubes Withdrawn EP2392780A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/791,056 US20110293407A1 (en) 2010-06-01 2010-06-01 Seal and airfoil tip clearance control

Publications (2)

Publication Number Publication Date
EP2392780A2 true EP2392780A2 (fr) 2011-12-07
EP2392780A3 EP2392780A3 (fr) 2014-11-05

Family

ID=44118077

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11168277.9A Withdrawn EP2392780A3 (fr) 2010-06-01 2011-05-31 Dispositif d'étanchéité et réglage du jeu des extrémités d'aubes

Country Status (2)

Country Link
US (1) US20110293407A1 (fr)
EP (1) EP2392780A3 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014052345A1 (fr) * 2012-09-27 2014-04-03 United Technologies Corporation Joint à air intérieur annulaire complet avec écrou de verrouillage

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8961115B2 (en) * 2012-07-19 2015-02-24 United Technologies Corporation Clearance control for gas turbine engine seal
US9255524B2 (en) 2012-12-20 2016-02-09 United Technologies Corporation Variable outer air seal fluid control
EP2971592B1 (fr) 2013-03-11 2020-10-07 United Technologies Corporation Actionneur pour joint d' étanche extérieur d'une aube de moteur à turbine à gaz
WO2014186003A2 (fr) * 2013-04-12 2014-11-20 United Technologies Corporation Système de commande de jeu à réponse rapide de carter de turbine à volume variable
US11248485B1 (en) 2020-08-17 2022-02-15 General Electric Company Systems and apparatus to control deflection mismatch between static and rotating structures

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2195715B (en) * 1986-10-08 1990-10-10 Rolls Royce Plc Gas turbine engine rotor blade clearance control
US5344284A (en) * 1993-03-29 1994-09-06 The United States Of America As Represented By The Secretary Of The Air Force Adjustable clearance control for rotor blade tips in a gas turbine engine
GB2310255B (en) * 1996-02-13 1999-06-16 Rolls Royce Plc A turbomachine
GB2388407B (en) * 2002-05-10 2005-10-26 Rolls Royce Plc Gas turbine blade tip clearance control structure
GB2404953A (en) * 2003-08-15 2005-02-16 Rolls Royce Plc Blade tip clearance system
FR2906295B1 (fr) * 2006-09-22 2011-11-18 Snecma Dispositif de toles isolantes sur carter pour amelioration du jeu en sommet d'aube
US8268032B2 (en) * 2008-07-07 2012-09-18 General Electric Company Gasket for providing a seal between two objects

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014052345A1 (fr) * 2012-09-27 2014-04-03 United Technologies Corporation Joint à air intérieur annulaire complet avec écrou de verrouillage
US9327368B2 (en) 2012-09-27 2016-05-03 United Technologies Corporation Full ring inner air-seal with locking nut

Also Published As

Publication number Publication date
US20110293407A1 (en) 2011-12-01
EP2392780A3 (fr) 2014-11-05

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