US20110293407A1 - Seal and airfoil tip clearance control - Google Patents

Seal and airfoil tip clearance control Download PDF

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Publication number
US20110293407A1
US20110293407A1 US12/791,056 US79105610A US2011293407A1 US 20110293407 A1 US20110293407 A1 US 20110293407A1 US 79105610 A US79105610 A US 79105610A US 2011293407 A1 US2011293407 A1 US 2011293407A1
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US
United States
Prior art keywords
housing
flex beam
set forth
blade outer
outer air
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.)
Abandoned
Application number
US12/791,056
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.)
Raytheon Technologies 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
Priority to US12/791,056 priority Critical patent/US20110293407A1/en
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WAGNER, JOEL H.
Priority to EP11168277.9A priority patent/EP2392780A3/en
Publication of US20110293407A1 publication Critical patent/US20110293407A1/en
Abandoned 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 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 is a cross-sectional view through a first embodiment.
  • FIG. 2 is a view along line 2 - 2 as shown in FIG. 1 .
  • FIG. 3 shows a perspective view of a component.
  • FIG. 4 shows a second embodiment
  • FIG. 1 A portion of a turbine section 20 of a gas turbine engine is illustrated in FIG. 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 FIG. 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 .
  • FIG. 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 .
  • FIG. 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.
  • FIGS. 1 and 4 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.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A turbine section includes a housing and a blade outer air seal to be mounted on the housing. A flex beam mounts 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.

Description

    BACKGROUND
  • Gas turbine engines are known and 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.
  • In the design of gas turbine rotors, it is desired to ensure that the bulk of the products of combustion pass across the turbine rotors. Thus, 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. However, various factors raise challenges with maintaining this clearance. In the past, various ways for adjusting this clearance such as the use of thermal control methods have been proposed.
    • SUMMARY
  • A turbine section 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.
  • These and other features of the present invention can be best understood from the following specification and drawings, the following of which is a brief description.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 is a cross-sectional view through a first embodiment.
  • FIG. 2 is a view along line 2-2 as shown in FIG. 1.
  • FIG. 3 shows a perspective view of a component.
  • FIG. 4 shows a second embodiment.
    •  DETAILED DESCRIPTION
  • A portion of a turbine section 20 of a gas turbine engine is illustrated in FIG. 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. Of course, 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.
  • During operation of the gas turbine engine, 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. Thus, 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. Additionally, 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. On the other hand, 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 FIG. 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.
  • FIG. 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.
  • FIG. 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.
  • As can be appreciated from both FIGS. 1 and 4, 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.
  • Although embodiments of this invention have been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of this invention. For that reason, the following claims should be studied to determine the true scope and content of this invention.

Claims (20)

1. A housing section for a gas turbine engine comprising:
a housing;
a flex beam mounting a blade outer air seal onto said housing, with said flex beam being supported on said housing, and free to move relative to said housing; and
a pressure chamber formed on an opposed side of said flex beam from said blade outer air seal, and a source of pressurized air to be delivered into said pressure chamber to cause said flex beam to move said blade outer air seal toward and away from a central axis of said housing.
2. The housing as set forth in claim 1, wherein said source of pressurized air includes a valve controlled by a controller to control the pressure of air delivered into said pressure chamber.
3. The housing as set forth in claim 1, wherein said flex beam is supported within said housing at axially upstream and downstream ends, but free to move in an axial direction.
4. The housing as set forth in claim 3, wherein a seal is positioned between said flex beam and said housing.
5. The housing as set forth in claim 4, wherein said seal on said flex beam extends along at least one axial side of said flex beam, and at least a portion of two circumferential edges.
6. The housing as set forth in claim 1, wherein said flex beam removably mounts said blade outer air seal.
7. The housing as set forth in claim 1, wherein said flex beam includes a two-bar connection which guides said flex beam during flexing movement relative to said housing.
8. The housing as set forth in claim 1, wherein there are a plurality of adjacent flex beam portions extending over a portion of a circumferential extent of the housing.
9. The housing as set forth in claim 8, wherein each of said flex beam portions have opposed circumferential edges that interfit with an adjacent one of said flex beams, and a seal positioned between said circumferential edges.
10. The housing as set forth in claim 1, wherein said housing is utilized as part of a turbine section in a gas turbine engine.
11. The housing as set forth in claim 1, wherein a space is defined radially between a side of said flex beam which faces said blade outer air seal, and a radially outer portion of said blade outer air seal to facilitate radially inward flexing of the flex beam.
12. The housing as set forth in claim 11, wherein said flex beam is relatively thin at least in an area aligned with said space, and between 0.030-0.050 inches.
13. A turbine section for a gas turbine engine comprising:
a turbine rotor carrying a plurality of blades, said blades having a radial outer tip;
a housing;
a flex beam removably mounting a blade outer air seal onto said housing, with said flex beam being supported on said housing, but free to move relative to said housing;
a pressure chamber formed on an opposed side of said flex beam from said blade outer air seal, and a source of pressurized air to be delivered into said chamber to cause said flex beam to move said blade outer air seal toward and away from a central axis of said housing; and
said source of pressurized air includes a valve controlled by an controller to control the pressure of air delivered into said pressure chamber.
14. The turbine section as set forth in claim 13, wherein said flex beam is supported within said housing at axially upstream and downstream ends, but free to move in an axial direction.
15. The turbine section as set forth in claim 13, wherein a seal is positioned between said flex beam and said housing.
16. The turbine section as set forth in claim 15, wherein said seal on said flex beam extends along at least one axial side of said flex beam, and at least a portion of two circumferential edges.
17. The turbine section as set forth in claim 13, wherein said flex beam includes a two-bar connection which guides said flex beam during flexing movement relative to said housing.
18. The turbine section as set forth in claim 13, wherein there are a plurality of adjacent flex beam portions extending over a portion of a circumferential extent of the housing.
19. The turbine section as set forth in claim 13, wherein a space is defined radially between the face of said flex beam which faces said blade outer air seal, and a radially outer portion of said blade outer air seal to facilitate radially inward flexing of the flex beam, said flex beam is relatively thin at least in an area aligned with said space, and between 0.030-0.050 inches.
20. A turbine section for a gas turbine engine comprising:
a turbine rotor carrying a plurality of blades, said blades having a radial outer tip;
a housing;
a plurality of adjacent flex beam portions extending over a portion of a circumferential extent of the housing, each of said flex beam portions removably mounting a blade outer air seal portion onto said housing, with said flex beam portions being supported on said housing, but free to move relative to said housing;
a pressure chamber formed on an opposed side of each said flex beam portion from said blade outer air seal portions, and a source of pressurized air to be delivered into said pressure chamber to cause said flex beam portion to move said blade outer air seal toward and away from a central axis of said housing;
said source of pressurized air includes a valve controlled by a controller to control the pressure of air delivered into said pressure chamber;
a space defined radially between a side face of said flex beam which faces said blade outer air seal portion, and a radially outer portion of said blade outer air seal portion to facilitate radially inward flexing of the flex beam; and
said flex beam portion is relatively thin at least in an area aligned with said space, and between 0.030-0.050 inches.
US12/791,056 2010-06-01 2010-06-01 Seal and airfoil tip clearance control Abandoned US20110293407A1 (en)

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140020390A1 (en) * 2012-07-19 2014-01-23 William E. Rhoden Clearance control for gas turbine engine seal
WO2014099259A1 (en) * 2012-12-20 2014-06-26 United Technologies Corporation Variable outer air seal fluid control
WO2014186015A3 (en) * 2013-03-11 2015-02-26 United Technologies Corporation Actuator for gas turbine engine blade outer air seal
WO2014186003A3 (en) * 2013-04-12 2015-02-26 United Technologies Corporation Gas turbine engine rapid response clearance control system with variable volume turbine case
US11248485B1 (en) 2020-08-17 2022-02-15 General Electric Company Systems and apparatus to control deflection mismatch between static and rotating structures

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9327368B2 (en) 2012-09-27 2016-05-03 United Technologies Corporation Full ring inner air-seal with locking nut

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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
US5772400A (en) * 1996-02-13 1998-06-30 Rolls-Royce Plc Turbomachine
US20080075584A1 (en) * 2006-09-22 2008-03-27 Snecma Set of insulating sheets on a casing to improve blade tip clearance
US20100001477A1 (en) * 2008-07-07 2010-01-07 General Electric Company Gasket for providing a seal between two objects

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GB2195715B (en) * 1986-10-08 1990-10-10 Rolls Royce Plc Gas turbine engine rotor blade clearance control
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

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Publication number Priority date Publication date Assignee Title
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
US5772400A (en) * 1996-02-13 1998-06-30 Rolls-Royce Plc Turbomachine
US20080075584A1 (en) * 2006-09-22 2008-03-27 Snecma Set of insulating sheets on a casing to improve blade tip clearance
US20100001477A1 (en) * 2008-07-07 2010-01-07 General Electric Company Gasket for providing a seal between two objects

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140020390A1 (en) * 2012-07-19 2014-01-23 William E. Rhoden Clearance control for gas turbine engine seal
US8961115B2 (en) * 2012-07-19 2015-02-24 United Technologies Corporation Clearance control for gas turbine engine seal
WO2014099259A1 (en) * 2012-12-20 2014-06-26 United Technologies Corporation Variable outer air seal fluid control
US9255524B2 (en) 2012-12-20 2016-02-09 United Technologies Corporation Variable outer air seal fluid control
WO2014186015A3 (en) * 2013-03-11 2015-02-26 United Technologies Corporation Actuator for gas turbine engine blade outer air seal
US10066497B2 (en) 2013-03-11 2018-09-04 United Technologies Corporation Actuator for gas turbine engine blade outer air seal
US10815815B2 (en) 2013-03-11 2020-10-27 Raytheon Technologies Corporation Actuator for gas turbine engine blade outer air seal
WO2014186003A3 (en) * 2013-04-12 2015-02-26 United Technologies Corporation Gas turbine engine rapid response clearance control system with variable volume turbine case
US10557368B2 (en) 2013-04-12 2020-02-11 United Technologies Corporation Gas turbine engine rapid response clearance control system with variable volume turbine case
US11248485B1 (en) 2020-08-17 2022-02-15 General Electric Company Systems and apparatus to control deflection mismatch between static and rotating structures

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Publication number Publication date
EP2392780A3 (en) 2014-11-05
EP2392780A2 (en) 2011-12-07

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Owner name: UNITED TECHNOLOGIES CORPORATION, CONNECTICUT

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:WAGNER, JOEL H.;REEL/FRAME:024461/0346

Effective date: 20100524

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION