US3765791A - Turbine nozzle support - Google Patents

Turbine nozzle support Download PDF

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Publication number
US3765791A
US3765791A US00196656A US3765791DA US3765791A US 3765791 A US3765791 A US 3765791A US 00196656 A US00196656 A US 00196656A US 3765791D A US3765791D A US 3765791DA US 3765791 A US3765791 A US 3765791A
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US
United States
Prior art keywords
guide vane
arrangement according
gas
turbo
assembly
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.)
Expired - Lifetime
Application number
US00196656A
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English (en)
Inventor
K Trappmann
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.)
MTU Aero Engines AG
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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 MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Application granted granted Critical
Publication of US3765791A publication Critical patent/US3765791A/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators

Definitions

  • the present invention relates to a mounting support for a turbine nozzle, and more particularly to a mounting support of a turbine guide-vane ring connected to a gas channel, especially to a hot gas scroll, in the end section of a turbo group which is axially yieldingly con nected at this end section with an adjacent structural group by way of a plug-in connection.
  • the guide ring is rigidly connected at its inner ring or shroud with a housing of the turbo group whereas it is held axially movably with its outer ring or shroud in a collar of the gas channel which itself is supported at the adjacent structural group, whereby the outer ring or shroud in the collar forms together with an annular piston a structural unit whose end surface facing upstream is acted upon by the gas pressure prevailing upstream of the guide ring whereas in part a high compressor endpressure and in part the pressure prevailing downstream of the turbine acts on the end surface facing downstream.
  • the subdivision of the piston area is thereby so selected in an advantageous manner that a support force results at the outer ring or shroud which is oppositely directed to the axial load of the blades by the pressure decrease at the cascade.
  • a force equilibrium is created thereby at the outer ring or shroud of the guide ring so that the mounting of the turbine guide ring represents in practice a clamping of the guide blades on both sides.
  • the adaptation of the piston ring areas to the three pressures can thereby take place both by calculation as well as by experiments.
  • FIGURE is a partial longitudinal axial cross-sectional view through a mounting support of a turbine guide-blade ring in accordance with the present invention.
  • a gas producer assembly 1 is partially shown in this figure, which is connected by a plug-in connection of conventional type with a power turbine assembly 2.
  • Working gases flow out of a hot gas channel or duct 9 through a turbine nozzle, i.e., the guide-vane ring provided withguide blades 6 and act upon a turbine wheel 11 from where they are fed to the power turbine assembly 2.
  • the hot gas duct 9 is securely connected at its inner diameter to an internal flange 8 of the gas producer housing.
  • the hot gas duct 9' is supported by way of a collar 3 at a flange 12 of the power turbine assembly 2.
  • the guide vanes 6 arranged downstream of the hot gas duct 9 form together with an inner ring or shroud 7, which is rigidly connected with the housing flange 8, a turbine nozzle and more particularly a guide-vane ring.
  • An outer ring or shroud 5 of this guide ring is held radially slidably with its nose portion 15 in a groove 16 of a flange constructed as a piston 13.
  • the piston 13 is axially movable in the collar 3.
  • the piston 13 terminates in a connecting ring 14, by means of which the plug-in connection with the housing 4 of the power turbine assembly 2 is established.
  • Piston rings 10 are thereby provided as sealing elements.
  • these loads are equalized in such a manner that the piston surface 17 facing downstream is acted upon by a high compressor end-pressure P, in that a connection 16 to a pressure space of the compressor end-pressure P, is provided.
  • the piston ring surface 17 acted upon by this compressor end-pressure P extends from d, to d
  • the axial area between d, and d is acted upon by the low pressure P, downstream of the turbine.
  • the dimensions d,,, d d and d of the guide ring support are so matched to one another and to the pressures P Py and P, that a total axial load results in the normal operating range at the outer ring or shroud 5 which is equal to zero so that neither bending nor shear loads are transmitted to the blades 6.
  • first connecting-means rigidly connecting one of said inner and outer guide vane rings to said housing means
  • second connecting means interposed between the other of said inner and outer guide vane rings and said collar means for supporting said other of said inner and outer guide vane rings at said collar means
  • said second connecting means including piston means axially fixed to said other of said inner and outer guide vane rings and axially movably supported in said collar means, said piston means having respective upstream and downstream facing end surfaces with respect to gas flow through said turbo-assembly, said upstream facing end surface being acted upon by the gas pressure prevailing immediately upstream of said guide vane means, at least a portion of said downstream facing end surface being acted upon by the gas pressure prevailing immediatley downstream of said turbine unit, and
  • high pressure communicating means for communicating high pressure gas under a pressure higher than the pressure prevailing immediately downstream of said turbine unit directly with at least a portion of said downstream facing end surface, whereby said high pressure gas and the gas pressure prevailing immediately downstream of said turbine unit counteracts at least a part of the bending forces on the guide vane means resulting from movement of said piston means due to pressure forces on said upstream facing end surface during operation of said turbo-assembly.
  • said high pressure communicating means includes means for conducting said high pressure gas from a high pressure compressor of said turbo-assembly which is arranged downstream of said turbine unit.
  • said high pressure communicating means includes means for conducting said high pressure gas from a high pressure compressor of said turbo-assembly which is arranged downstream of said turbine unit.
  • said plug-type connecting means includes an extension on said piston means which axially and yieldingly engages in a corresponding opening of said next adjacent portion.
  • said plug-type connecting means includes an extension on said piston means which axially and yieldingly engages in a corresponding opening of said next adjacent portion.
  • said high pressure communicating means includes means for conducting said high pressure gas from a high pressure compressor of said turbo-assembly which is arranged downstream of said turbine unit.
  • said plug-type connecting means includes an extension on said piston means which axially and yieldingly engages in a corresponding opening of said next adjacent portion.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US00196656A 1970-11-07 1971-11-08 Turbine nozzle support Expired - Lifetime US3765791A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19702054926 DE2054926B2 (de) 1970-11-07 1970-11-07 Halterung eines turbinenleitkranzes

Publications (1)

Publication Number Publication Date
US3765791A true US3765791A (en) 1973-10-16

Family

ID=5787498

Family Applications (1)

Application Number Title Priority Date Filing Date
US00196656A Expired - Lifetime US3765791A (en) 1970-11-07 1971-11-08 Turbine nozzle support

Country Status (4)

Country Link
US (1) US3765791A (OSRAM)
DE (1) DE2054926B2 (OSRAM)
FR (1) FR2112872A5 (OSRAM)
GB (1) GB1368770A (OSRAM)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4274805A (en) * 1978-10-02 1981-06-23 United Technologies Corporation Floating vane support
US4566851A (en) * 1984-05-11 1986-01-28 United Technologies Corporation First stage turbine vane support structure
US4815933A (en) * 1987-11-13 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Nozzle flange attachment and sealing arrangement
US4883405A (en) * 1987-11-13 1989-11-28 The United States Of America As Represented By The Secretary Of The Air Force Turbine nozzle mounting arrangement
EP1426561A3 (en) * 2002-11-27 2005-05-25 General Electric Company Structures for attaching or sealing a space between components having different coefficients or rates of thermal expansion
US20090246012A1 (en) * 2008-03-31 2009-10-01 General Electric Company Turbine stator mount
US20090246014A1 (en) * 2008-03-31 2009-10-01 General Electric Company method and system for supporting stator components
US20150044054A1 (en) * 2013-03-15 2015-02-12 Rolls-Royce North American Technologies, Inc. Composite retention feature
US20160177773A1 (en) * 2014-12-19 2016-06-23 Schlumberger Technology Corporation Apparatus for Extending the Flow Range of Turbines
US20180087395A1 (en) * 2016-09-23 2018-03-29 Rolls-Royce Plc Gas turbine engine
CN112302738A (zh) * 2020-09-30 2021-02-02 北京航天动力研究所 一种用于高压力涡轮进气壳体结构的柔性、力分类方法

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4478551A (en) * 1981-12-08 1984-10-23 United Technologies Corporation Turbine exhaust case design
US6884026B2 (en) * 2002-09-30 2005-04-26 General Electric Company Turbine engine shroud assembly including axially floating shroud segment

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3129922A (en) * 1961-11-27 1964-04-21 Frederick A Rosenthal Self centering ring seal
US3391904A (en) * 1966-11-02 1968-07-09 United Aircraft Corp Optimum response tip seal
US3520635A (en) * 1968-11-04 1970-07-14 Avco Corp Turbomachine shroud assembly
US3623736A (en) * 1968-09-26 1971-11-30 Rolls Royce Sealing device

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3129922A (en) * 1961-11-27 1964-04-21 Frederick A Rosenthal Self centering ring seal
US3391904A (en) * 1966-11-02 1968-07-09 United Aircraft Corp Optimum response tip seal
US3623736A (en) * 1968-09-26 1971-11-30 Rolls Royce Sealing device
US3520635A (en) * 1968-11-04 1970-07-14 Avco Corp Turbomachine shroud assembly

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4274805A (en) * 1978-10-02 1981-06-23 United Technologies Corporation Floating vane support
US4566851A (en) * 1984-05-11 1986-01-28 United Technologies Corporation First stage turbine vane support structure
US4815933A (en) * 1987-11-13 1989-03-28 The United States Of America As Represented By The Secretary Of The Air Force Nozzle flange attachment and sealing arrangement
US4883405A (en) * 1987-11-13 1989-11-28 The United States Of America As Represented By The Secretary Of The Air Force Turbine nozzle mounting arrangement
EP1426561A3 (en) * 2002-11-27 2005-05-25 General Electric Company Structures for attaching or sealing a space between components having different coefficients or rates of thermal expansion
US8172522B2 (en) 2008-03-31 2012-05-08 General Electric Company Method and system for supporting stator components
US20090246014A1 (en) * 2008-03-31 2009-10-01 General Electric Company method and system for supporting stator components
US8092163B2 (en) 2008-03-31 2012-01-10 General Electric Company Turbine stator mount
US20090246012A1 (en) * 2008-03-31 2009-10-01 General Electric Company Turbine stator mount
US20150044054A1 (en) * 2013-03-15 2015-02-12 Rolls-Royce North American Technologies, Inc. Composite retention feature
US9506356B2 (en) * 2013-03-15 2016-11-29 Rolls-Royce North American Technologies, Inc. Composite retention feature
US20160177773A1 (en) * 2014-12-19 2016-06-23 Schlumberger Technology Corporation Apparatus for Extending the Flow Range of Turbines
US9840933B2 (en) * 2014-12-19 2017-12-12 Schlumberger Technology Corporation Apparatus for extending the flow range of turbines
US20180087395A1 (en) * 2016-09-23 2018-03-29 Rolls-Royce Plc Gas turbine engine
CN112302738A (zh) * 2020-09-30 2021-02-02 北京航天动力研究所 一种用于高压力涡轮进气壳体结构的柔性、力分类方法
CN112302738B (zh) * 2020-09-30 2023-03-07 北京航天动力研究所 一种用于高压力涡轮进气壳体结构的柔性、力分类方法

Also Published As

Publication number Publication date
DE2054926B2 (de) 1972-02-03
GB1368770A (en) 1974-10-02
DE2054926A1 (OSRAM) 1972-02-03
FR2112872A5 (OSRAM) 1972-06-23

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