WO2014068355A1 - Système d'échappement de moteur de turbine à gaz et procédé correspondant d'accès aux aubes de turbine - Google Patents

Système d'échappement de moteur de turbine à gaz et procédé correspondant d'accès aux aubes de turbine Download PDF

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Publication number
WO2014068355A1
WO2014068355A1 PCT/IB2012/002841 IB2012002841W WO2014068355A1 WO 2014068355 A1 WO2014068355 A1 WO 2014068355A1 IB 2012002841 W IB2012002841 W IB 2012002841W WO 2014068355 A1 WO2014068355 A1 WO 2014068355A1
Authority
WO
WIPO (PCT)
Prior art keywords
exhaust system
diffuser section
exhaust
seal
circumferential groove
Prior art date
Application number
PCT/IB2012/002841
Other languages
English (en)
Inventor
Robert JAMIOLKOWSKI
Piotr Edward KOBEK
Przemyslaw JAKUBCZAK
Original Assignee
General Electric Company
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 General Electric Company filed Critical General Electric Company
Priority to PCT/IB2012/002841 priority Critical patent/WO2014068355A1/fr
Priority to CN201280076814.2A priority patent/CN104769235A/zh
Publication of WO2014068355A1 publication Critical patent/WO2014068355A1/fr

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/70—Disassembly methods
    • 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
    • F05D2260/02—Transport and handling during maintenance and repair

Definitions

  • Embodiments of the present disclosure relate generally to gas turbine engines and more particularly to exhaust systems and methods for facilitating access to one or more turbine buckets.
  • a conventional gas turbine engine may include a compressor, a combustor, and a turbine.
  • the compressor may supply compressed air to the combustor, where the compressed air may be mixed with fuel and burned to generate a hot gas.
  • This hot gas may be supplied to the turbine, where energy may be extracted from the hot gas to produce work.
  • the turbine may include one or more turbine buckets which rotate as the hot gas passes therethrough. The hot gas may exit the turbine via an exhaust system.
  • an exhaust system for a gas turbine engine may include an inner diffuser section having a forward portion and an aft portion.
  • the system may also include a circumferential groove disposed in the aft portion.
  • the system may include a boss disposed in the forward portion. In this manner, the boss may be configured to mate with the circumferential groove to attach the forward portion to the aft portion in a removable configuration.
  • an exhaust system for a gas turbine engine may include an inner diffuser section having a forward portion and an aft portion.
  • the system may also include a rabbet joint configured to attach the forward portion to the aft portion.
  • a method for accessing one or more turbine buckets may include removing an exhaust frame forward casing.
  • the method may also include removing a forward portion of an outer diffuser section.
  • the method may include removing a forward portion of an inner diffuser section.
  • FIG. 1 is a schematic of an example diagram of a gas turbine engine with a compressor, a combustor, and a turbine, according to an embodiment of the disclosure.
  • FIG. 2 is a cross sectional view of a portion of an exhaust system, according to an embodiment of the disclosure.
  • FIG. 3 is a cross sectional view of a portion of an exhaust system, according to an embodiment of the disclosure.
  • Illustrative embodiments are directed to, among other things, gas turbine engines including exhaust systems and methods for facilitating access to one or more turbine buckets.
  • certain embodiments of the disclosure may facilitate accessing one or more turbine buckets, particularly the last stage turbine buckets, via the exhaust system.
  • the various components described herein may be detachable and/or removable from the exhaust system. That is, in one embodiment, an exhaust frame forward casing, a forward portion of the outer diffuser section, and a forward portion of the inner diffuser section may be removed in order to provide access to (or removal of) the last stage turbine buckets.
  • the exhaust system may include an inner diffuser section having a forward portion and an aft portion.
  • the forward portion of the inner diffuser section and the aft portion of the inner diffuser section may be removeably attached to each other via a rabbet joint.
  • the rabbet joint may include a circumferential groove disposed in the aft portion of the inner diffuser section and a boss disposed in the forward portion of the inner diffuser section. In this manner, the boss may be configured to mate with the circumferential groove.
  • a retaining ring may be positioned adjacent to the circumferential groove to secure the boss within the circumferential groove.
  • the exhaust system may also include a primary seal positioned adjacent to the circumferential groove to form a seal between an exhaust frame and the inner diffuser section.
  • a slot may be associated with the aft portion of the inner diffuser section such that at least a portion of the primary seal may be disposed within the slot.
  • the exhaust system may include a secondary seal positioned adjacent to a forward end of the forward portion of the inner diffuser section. The secondary sea! may form a seal between the exhaust frame and the inner diffuser section.
  • a slot may be associated with the forward portion of the inner diffuser section such that at least a portion of the secondary seal is disposed within the slot.
  • the exhaust system may include an outer diffuser section having a forward portion attached to an aft portion.
  • the exhaust system may include an exhaust frame forward casing disposed about the inner diffuser section and the outer diffuser section.
  • the exhaust frame forward casing may include a shell that is attached (e.g., bolted) to a turbine shell at one end and to the exhaust frame at the other end.
  • the exhaust system may include an outer forward seal positioned adjacent to a forward end of the forward portion of the outer diffuser section to form a seal between the exhaust frame forward casing and the outer diffuser section.
  • the gas turbine engine 10 may include a compressor 15.
  • the compressor 15 may compress an incoming flow of air 20.
  • the compressor 15 may deliver the compressed flow of air 20 to a combustor 25.
  • the combustor 25 may mix the compressed flow of air 20 with a pressurized flow of fuel 30 and ignite the mixture to create a flow of combustion gases 35.
  • the gas turbine engine 10 may include any number of combustors 25.
  • the flow of combustion gases 35 in turn may be delivered to a turbine 40.
  • the flow of combustion gases 35 may drive the turbine 40 so as to produce mechanical work.
  • the mechanical work produced in the turbine 40 may drive the compressor 15 via a shaft 45 and an external load 50 such as an electrical generator or the like.
  • the gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels.
  • the gas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, New York, including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine or the like.
  • the gas turbine engine 10 may have different configurations and may use other types of components.
  • other types of gas turbine engines also may be used herein.
  • Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.
  • the gas turbine engine 10 may include an exhaust system 100.
  • the exhaust system 100 may include an exhaust frame 102.
  • the exhaust frame 102 may support (directly or indirectly) various components of the exhaust system 100.
  • the exhaust system 100 may also include an exhaust frame forward casing 104.
  • the exhaust frame forward casing 104 may be attached (e.g., by bolts 106) to a turbine shell 108 at one end and to the exhaust frame 102 at the other end.
  • the exhaust frame forward casing 104 may be formed of several components, such as two 180 degree shells secured together.
  • the exhaust frame forward casing 104 may be a single component or multiple components. In this manner, the exhaust frame forward casing 104 may be detached from the turbine shell 108 and the exhaust frame 102 to provide access to internal portions of the exhaust system 100.
  • the exhaust system 100 may also include an outer diffuser section 110.
  • the outer diffuser section 110 may include an aft portion 112 and a forward portion 114.
  • the aft portion 112 of the outer diffuser section 110 and the forward portion 114 of the outer diffuser section 110 may be secured together (e.g., by bolt 116) so as to form a continuous flow path for the combustion hot gasses when assembled.
  • the exhaust system 100 may include an outer forward seal 118 positioned between the forward portion 114 of the outer diffuser section 110 and the exhaust frame forward casing 104.
  • the outer forward seal 118 may be held in place by a radial slot 120 associated with the forward portion 114 of the outer diffuser section 110 and a radial slot 122 associated with the exhaust frame forward casing 104. Any securing means may be used to fasten the outer forward seal 118 in place.
  • the outer forward seal 118 may be removed from radial slots 120 and 122.
  • the forward portion 114 of the outer diffuser section 110 may be detached from the aft portion 112 of the outer diffuser section 110 and removed.
  • the exhaust system 100 may include an inner diffuser section 124.
  • the inner diffuser section 124 may include an aft portion 126 and a forward portion 128.
  • the aft portion 126 of the inner diffuser section 124 and the forward portion 128 of the inner diffuser section 124 may be secured together by a rabbet joint 130 so as to from a continuous flow path for the combustion hot gasses when assembled.
  • the rabbet joint 130 may include a circumferential groove 132 disposed in the aft portion 128 of the inner diffuser section 124.
  • the rabbet joint 130 may include a boss 134 disposed in the forward portion 126 of the inner diffuser section 124.
  • the boss 134 may be configured to mate with the circumferential groove 132, for example, in a hooking manner.
  • the exhaust system 100 may also include a retaining ring 136 positioned adjacent to the circumferential groove 132 and boss 134 to secure the boss 134 within the circumferential groove 132.
  • the exhaust system 100 may include a primary seal 138 positioned adjacent to the circumferential groove 132 to form a seal between the exhaust frame 102 and the inner diffuser section 124.
  • the primary seal 138 may be secured in place by a radial slot 140 associated with the aft portion 126 of the inner diffuser 124 and a bolt 142 associated with the exhaust frame 102. Any securing means, however, may be used to fasten the primary seal 138 in place.
  • the exhaust system 100 may include a secondary seal 144 positioned adjacent to a forward end of the forward portion 128 of the inner diffuser section 124 to form a seal between the exhaust frame 102 and the inner diffuser section 124.
  • the secondary seal may be secured in place by an axial slot 146 associated with the forward portion 128 of the inner diffuser section 124 and a radial slot 148 associated with a removable ring 150.
  • the forward portion 128 of the inner diffuser section 124 may be removed from the exhaust system 100 by removing the retaining ring 136 and then disengaging the forward portion 128 of the inner diffuser section 124 from the primary seal 138 and the secondary seal 144. Moreover, the removable ring 150 may be removed to provide access to a cavity 152 for turbine bucket 154 removal. For example, the removable of the exhaust frame forward casing 104, the forward portion 114 of the outer diffuser section 11, the forward portion 128 of the inner diffuser section 124, and the removable ring 150 may provide a space to allow the last stage turbine buckets 154 to be pulled out of the rotor wheel from the aft side of the turbine casing for maintenance and/or replacement.

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

Abstract

Selon un mode de réalisation, la présente invention concerne un système d'échappement destiné à un moteur de turbine à gaz. Le système peut comprendre une section de diffuseur interne dotée d'une partie avant et d'une partie arrière. Le système peut également comprendre une rainure circonférentielle disposée dans la partie arrière. En outre, le système peut comprendre un bossage disposé dans la partie avant. De cette manière, le bossage peut être conçu pour s'accoupler à la rainure circonférentielle de sorte à fixer la partie avant à la partie arrière selon une configuration amovible. L'invention concerne également un procédé correspondant d'accès aux aubes de turbine.
PCT/IB2012/002841 2012-10-30 2012-10-30 Système d'échappement de moteur de turbine à gaz et procédé correspondant d'accès aux aubes de turbine WO2014068355A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/IB2012/002841 WO2014068355A1 (fr) 2012-10-30 2012-10-30 Système d'échappement de moteur de turbine à gaz et procédé correspondant d'accès aux aubes de turbine
CN201280076814.2A CN104769235A (zh) 2012-10-30 2012-10-30 燃气涡轮发动机排气系统和进入涡轮叶片的方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/IB2012/002841 WO2014068355A1 (fr) 2012-10-30 2012-10-30 Système d'échappement de moteur de turbine à gaz et procédé correspondant d'accès aux aubes de turbine

Publications (1)

Publication Number Publication Date
WO2014068355A1 true WO2014068355A1 (fr) 2014-05-08

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Family Applications (1)

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PCT/IB2012/002841 WO2014068355A1 (fr) 2012-10-30 2012-10-30 Système d'échappement de moteur de turbine à gaz et procédé correspondant d'accès aux aubes de turbine

Country Status (2)

Country Link
CN (1) CN104769235A (fr)
WO (1) WO2014068355A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2016044630A (ja) * 2014-08-25 2016-04-04 三菱日立パワーシステムズ株式会社 ガスタービンの排気部材及び排気室メンテナンス方法
EP3441578A1 (fr) * 2017-08-11 2019-02-13 General Electric Company Diffuseur d'échappement de turbine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10287920B2 (en) * 2015-11-24 2019-05-14 General Electric Company System of supporting turbine diffuser
JP5980405B1 (ja) * 2015-12-24 2016-08-31 三菱日立パワーシステムズ株式会社 翼の取外方法、この方法を実行するための装置及び治具、この装置を備える翼セット

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4391566A (en) * 1979-11-14 1983-07-05 Nissan Motor Co., Ltd. Diffuser and exhaust gas collector arrangement
US5104286A (en) * 1991-02-08 1992-04-14 Westinghouse Electric Corp. Recirculation seal for a gas turbine exhaust diffuser
US5346365A (en) * 1992-09-25 1994-09-13 Asea Brown Boveri Ltd. Gas turbine with exhaust gas casing and exhaust gas duct
JP2004011609A (ja) * 2002-06-11 2004-01-15 Toshiba Corp 蒸気タービン
US20090053046A1 (en) * 2007-08-23 2009-02-26 General Electric Company Method, system and apparatus for turbine diffuser sealing

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP4191552B2 (ja) * 2003-07-14 2008-12-03 三菱重工業株式会社 ガスタービン尾筒の冷却構造
FR2859762B1 (fr) * 2003-09-11 2006-01-06 Snecma Moteurs Realisation de l'etancheite pour le prelevement cabine par un joint segment
US7435050B2 (en) * 2006-01-11 2008-10-14 United Technologies Corporation Split flange V-groove and anti-rotation mating system
US8328513B2 (en) * 2009-12-31 2012-12-11 General Electric Company Systems and apparatus relating to compressor stator blades and diffusers in turbine engines

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4391566A (en) * 1979-11-14 1983-07-05 Nissan Motor Co., Ltd. Diffuser and exhaust gas collector arrangement
US5104286A (en) * 1991-02-08 1992-04-14 Westinghouse Electric Corp. Recirculation seal for a gas turbine exhaust diffuser
US5346365A (en) * 1992-09-25 1994-09-13 Asea Brown Boveri Ltd. Gas turbine with exhaust gas casing and exhaust gas duct
JP2004011609A (ja) * 2002-06-11 2004-01-15 Toshiba Corp 蒸気タービン
US20090053046A1 (en) * 2007-08-23 2009-02-26 General Electric Company Method, system and apparatus for turbine diffuser sealing

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2016044630A (ja) * 2014-08-25 2016-04-04 三菱日立パワーシステムズ株式会社 ガスタービンの排気部材及び排気室メンテナンス方法
EP3441578A1 (fr) * 2017-08-11 2019-02-13 General Electric Company Diffuseur d'échappement de turbine
KR20190017658A (ko) * 2017-08-11 2019-02-20 제네럴 일렉트릭 컴퍼니 터빈 배기가스 디퓨져
JP2019060336A (ja) * 2017-08-11 2019-04-18 ゼネラル・エレクトリック・カンパニイ タービン排気ディフューザ
US11215085B2 (en) 2017-08-11 2022-01-04 General Electric Company Turbine exhaust diffuser
JP7171297B2 (ja) 2017-08-11 2022-11-15 ゼネラル・エレクトリック・カンパニイ タービン排気ディフューザ
KR102604517B1 (ko) * 2017-08-11 2023-11-20 제네럴 일렉트릭 컴퍼니 터빈 배기가스 디퓨져

Also Published As

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