IT1317978B1 - Transition piece per camere di combustione di turbine a gas nonanulari. - Google Patents

Transition piece per camere di combustione di turbine a gas nonanulari.

Info

Publication number
IT1317978B1
IT1317978B1 IT2000MI001362A ITMI20001362A IT1317978B1 IT 1317978 B1 IT1317978 B1 IT 1317978B1 IT 2000MI001362 A IT2000MI001362 A IT 2000MI001362A IT MI20001362 A ITMI20001362 A IT MI20001362A IT 1317978 B1 IT1317978 B1 IT 1317978B1
Authority
IT
Italy
Prior art keywords
nonanular
combustion chambers
transition piece
gas turbines
turbines
Prior art date
Application number
IT2000MI001362A
Other languages
English (en)
Italian (it)
Inventor
Alessandro Coppola
Original Assignee
Nuovo Pignone Spa
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 Nuovo Pignone Spa filed Critical Nuovo Pignone Spa
Publication of ITMI20001362A0 publication Critical patent/ITMI20001362A0/it
Priority to IT2000MI001362A priority Critical patent/IT1317978B1/it
Priority to RU2003101058/06A priority patent/RU2275554C2/ru
Priority to MXPA02012451A priority patent/MXPA02012451A/es
Priority to PCT/EP2001/006484 priority patent/WO2001096712A1/en
Priority to AT01956465T priority patent/ATE310896T1/de
Priority to US10/311,251 priority patent/US20030167776A1/en
Priority to DE60115236T priority patent/DE60115236T2/de
Priority to EP01956465A priority patent/EP1295014B1/en
Priority to BR0111577-4A priority patent/BR0111577A/pt
Priority to AU78443/01A priority patent/AU7844301A/en
Priority to ARP010102872A priority patent/AR028133A1/es
Publication of ITMI20001362A1 publication Critical patent/ITMI20001362A1/it
Priority to NO20025995A priority patent/NO330416B1/no
Application granted granted Critical
Publication of IT1317978B1 publication Critical patent/IT1317978B1/it

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Gas Burners (AREA)
IT2000MI001362A 2000-06-16 2000-06-16 Transition piece per camere di combustione di turbine a gas nonanulari. IT1317978B1 (it)

Priority Applications (12)

Application Number Priority Date Filing Date Title
IT2000MI001362A IT1317978B1 (it) 2000-06-16 2000-06-16 Transition piece per camere di combustione di turbine a gas nonanulari.
DE60115236T DE60115236T2 (de) 2000-06-16 2001-06-08 Übergangstück für eine nicht-ringförmige gasturbinenbrennkammer
BR0111577-4A BR0111577A (pt) 2000-06-16 2001-06-08 Peça de transição para câmaras de combustão de turbina a gás não anulares
PCT/EP2001/006484 WO2001096712A1 (en) 2000-06-16 2001-06-08 Transition piece for non-annular gas turbine combustion chambers
AT01956465T ATE310896T1 (de) 2000-06-16 2001-06-08 Übergangstück für eine nicht-ringförmige gasturbinenbrennkammer
US10/311,251 US20030167776A1 (en) 2000-06-16 2001-06-08 Transition piece for non-annular gas turbine combustion chambers
RU2003101058/06A RU2275554C2 (ru) 2000-06-16 2001-06-08 Переходный элемент для некольцевых камер сгорания газовой турбины
EP01956465A EP1295014B1 (en) 2000-06-16 2001-06-08 Transition piece for non-annular gas turbine combustion chambers
MXPA02012451A MXPA02012451A (es) 2000-06-16 2001-06-08 Pieza de transicion para camaras de combusjtion de turbina a gas no anulares.
AU78443/01A AU7844301A (en) 2000-06-16 2001-06-08 Transition piece for non-annular gas turbine combustion chambers
ARP010102872A AR028133A1 (es) 2000-06-16 2001-06-15 Pieza de transicion para camaras de combustion no anulares en turbinas a gas
NO20025995A NO330416B1 (no) 2000-06-16 2002-12-13 Overgangsstykke for ikke-ringformede gassturbinforbrenningskamre

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
IT2000MI001362A IT1317978B1 (it) 2000-06-16 2000-06-16 Transition piece per camere di combustione di turbine a gas nonanulari.

Publications (3)

Publication Number Publication Date
ITMI20001362A0 ITMI20001362A0 (it) 2000-06-16
ITMI20001362A1 ITMI20001362A1 (it) 2001-12-16
IT1317978B1 true IT1317978B1 (it) 2003-07-21

Family

ID=11445283

Family Applications (1)

Application Number Title Priority Date Filing Date
IT2000MI001362A IT1317978B1 (it) 2000-06-16 2000-06-16 Transition piece per camere di combustione di turbine a gas nonanulari.

Country Status (12)

Country Link
US (1) US20030167776A1 (ru)
EP (1) EP1295014B1 (ru)
AR (1) AR028133A1 (ru)
AT (1) ATE310896T1 (ru)
AU (1) AU7844301A (ru)
BR (1) BR0111577A (ru)
DE (1) DE60115236T2 (ru)
IT (1) IT1317978B1 (ru)
MX (1) MXPA02012451A (ru)
NO (1) NO330416B1 (ru)
RU (1) RU2275554C2 (ru)
WO (1) WO2001096712A1 (ru)

Families Citing this family (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7178341B2 (en) * 2004-06-17 2007-02-20 Siemens Power Generation, Inc. Multi-zone tubing assembly for a transition piece of a gas turbine
US7278254B2 (en) * 2005-01-27 2007-10-09 Siemens Power Generation, Inc. Cooling system for a transition bracket of a transition in a turbine engine
US8015818B2 (en) * 2005-02-22 2011-09-13 Siemens Energy, Inc. Cooled transition duct for a gas turbine engine
US7827801B2 (en) * 2006-02-09 2010-11-09 Siemens Energy, Inc. Gas turbine engine transitions comprising closed cooled transition cooling channels
US8151570B2 (en) * 2007-12-06 2012-04-10 Alstom Technology Ltd Transition duct cooling feed tubes
US8113003B2 (en) * 2008-08-12 2012-02-14 Siemens Energy, Inc. Transition with a linear flow path for use in a gas turbine engine
US8091365B2 (en) * 2008-08-12 2012-01-10 Siemens Energy, Inc. Canted outlet for transition in a gas turbine engine
US20120186269A1 (en) * 2011-01-25 2012-07-26 General Electric Company Support between transition piece and impingement sleeve in combustor
KR101613096B1 (ko) * 2011-10-24 2016-04-20 제네럴 일렉트릭 테크놀러지 게엠베하 가스 터빈
US9593853B2 (en) * 2014-02-20 2017-03-14 Siemens Energy, Inc. Gas flow path for a gas turbine engine
WO2017039567A1 (en) * 2015-08-28 2017-03-09 Siemens Aktiengesellschaft Non-axially symmetric transition ducts for combustors
US10830442B2 (en) 2016-03-25 2020-11-10 General Electric Company Segmented annular combustion system with dual fuel capability
US10563869B2 (en) 2016-03-25 2020-02-18 General Electric Company Operation and turndown of a segmented annular combustion system
US10584880B2 (en) 2016-03-25 2020-03-10 General Electric Company Mounting of integrated combustor nozzles in a segmented annular combustion system
US11428413B2 (en) 2016-03-25 2022-08-30 General Electric Company Fuel injection module for segmented annular combustion system
US10520194B2 (en) 2016-03-25 2019-12-31 General Electric Company Radially stacked fuel injection module for a segmented annular combustion system
US10605459B2 (en) 2016-03-25 2020-03-31 General Electric Company Integrated combustor nozzle for a segmented annular combustion system
US10641175B2 (en) 2016-03-25 2020-05-05 General Electric Company Panel fuel injector
US10641491B2 (en) 2016-03-25 2020-05-05 General Electric Company Cooling of integrated combustor nozzle of segmented annular combustion system
US10584876B2 (en) 2016-03-25 2020-03-10 General Electric Company Micro-channel cooling of integrated combustor nozzle of a segmented annular combustion system
JP6650849B2 (ja) * 2016-08-25 2020-02-19 三菱日立パワーシステムズ株式会社 ガスタービン
US11156362B2 (en) 2016-11-28 2021-10-26 General Electric Company Combustor with axially staged fuel injection
US10690350B2 (en) 2016-11-28 2020-06-23 General Electric Company Combustor with axially staged fuel injection
US10837299B2 (en) * 2017-03-07 2020-11-17 General Electric Company System and method for transition piece seal
US11994292B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus for turbomachine
US11460191B2 (en) 2020-08-31 2022-10-04 General Electric Company Cooling insert for a turbomachine
US11994293B2 (en) 2020-08-31 2024-05-28 General Electric Company Impingement cooling apparatus support structure and method of manufacture
US11371702B2 (en) 2020-08-31 2022-06-28 General Electric Company Impingement panel for a turbomachine
US11614233B2 (en) 2020-08-31 2023-03-28 General Electric Company Impingement panel support structure and method of manufacture
US11255545B1 (en) 2020-10-26 2022-02-22 General Electric Company Integrated combustion nozzle having a unified head end
US11767766B1 (en) 2022-07-29 2023-09-26 General Electric Company Turbomachine airfoil having impingement cooling passages

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5964091A (en) * 1995-07-11 1999-10-12 Hitachi, Ltd. Gas turbine combustor and gas turbine
US6006523A (en) * 1997-04-30 1999-12-28 Mitsubishi Heavy Industries, Ltd. Gas turbine combustor with angled tube section
US6393828B1 (en) * 1997-07-21 2002-05-28 General Electric Company Protective coatings for turbine combustion components

Also Published As

Publication number Publication date
RU2275554C2 (ru) 2006-04-27
WO2001096712A1 (en) 2001-12-20
MXPA02012451A (es) 2003-04-25
ITMI20001362A1 (it) 2001-12-16
ITMI20001362A0 (it) 2000-06-16
AU7844301A (en) 2001-12-24
EP1295014A1 (en) 2003-03-26
EP1295014B1 (en) 2005-11-23
ATE310896T1 (de) 2005-12-15
DE60115236D1 (de) 2005-12-29
AR028133A1 (es) 2003-04-23
DE60115236T2 (de) 2006-07-27
BR0111577A (pt) 2003-03-18
NO20025995D0 (no) 2002-12-13
US20030167776A1 (en) 2003-09-11
NO330416B1 (no) 2011-04-11
NO20025995L (no) 2003-02-13

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