BR0111577A - Peça de transição para câmaras de combustão de turbina a gás não anulares - Google Patents
Peça de transição para câmaras de combustão de turbina a gás não anularesInfo
- Publication number
- BR0111577A BR0111577A BR0111577-4A BR0111577A BR0111577A BR 0111577 A BR0111577 A BR 0111577A BR 0111577 A BR0111577 A BR 0111577A BR 0111577 A BR0111577 A BR 0111577A
- Authority
- BR
- Brazil
- Prior art keywords
- gas turbine
- transition part
- annular gas
- turbine combustion
- combustion chambers
- Prior art date
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)
Abstract
"PEçA DE TRANSIçãO PARA CâMARAS DE COMBUSTãO DE TURBINA A GáS NãO ANULARES". Peça de transição (10) para câmaras de combustão de turbina a gás não anulares possui um braço de conexão projetante (22) para suporte sobre o estator de turbina, em que o braço de conexão projetante (22) toma possível se obter um eixo geométrico de fio de descida com um ângulo dentre 5<198> e 7<198> com relação a um eixo geométrico, que é paralelo ao eixo geométrico da máquina, e é perpendicular ao plano sobre o qual se assenta o quadro para a interface da peça de transição (10) com o anel de bocais do primeiro estágio da turbina a gás.
Applications Claiming Priority (2)
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. |
PCT/EP2001/006484 WO2001096712A1 (en) | 2000-06-16 | 2001-06-08 | Transition piece for non-annular gas turbine combustion chambers |
Publications (1)
Publication Number | Publication Date |
---|---|
BR0111577A true BR0111577A (pt) | 2003-03-18 |
Family
ID=11445283
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
BR0111577-4A BR0111577A (pt) | 2000-06-16 | 2001-06-08 | Peça de transição para câmaras de combustão de turbina a gás não anulares |
Country Status (12)
Country | Link |
---|---|
US (1) | US20030167776A1 (pt) |
EP (1) | EP1295014B1 (pt) |
AR (1) | AR028133A1 (pt) |
AT (1) | ATE310896T1 (pt) |
AU (1) | AU7844301A (pt) |
BR (1) | BR0111577A (pt) |
DE (1) | DE60115236T2 (pt) |
IT (1) | IT1317978B1 (pt) |
MX (1) | MXPA02012451A (pt) |
NO (1) | NO330416B1 (pt) |
RU (1) | RU2275554C2 (pt) |
WO (1) | WO2001096712A1 (pt) |
Families Citing this family (31)
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 |
US8091365B2 (en) * | 2008-08-12 | 2012-01-10 | Siemens Energy, Inc. | Canted outlet for transition in a gas turbine engine |
US8113003B2 (en) * | 2008-08-12 | 2012-02-14 | Siemens Energy, Inc. | Transition with a linear flow path for use 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 |
EP3341569A1 (en) * | 2015-08-28 | 2018-07-04 | Siemens Aktiengesellschaft | Non-axially symmetric transition ducts for combustors |
US10641491B2 (en) | 2016-03-25 | 2020-05-05 | General Electric Company | Cooling of integrated combustor nozzle of 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 |
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 |
US10584876B2 (en) | 2016-03-25 | 2020-03-10 | General Electric Company | Micro-channel cooling of integrated combustor nozzle of a segmented annular combustion system |
US10655541B2 (en) | 2016-03-25 | 2020-05-19 | General Electric Company | 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 |
US10605459B2 (en) | 2016-03-25 | 2020-03-31 | General Electric Company | Integrated combustor nozzle for 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 |
US11994293B2 (en) | 2020-08-31 | 2024-05-28 | General Electric Company | Impingement cooling apparatus support structure and method of manufacture |
US11460191B2 (en) | 2020-08-31 | 2022-10-04 | General Electric Company | Cooling insert for a turbomachine |
US11371702B2 (en) | 2020-08-31 | 2022-06-28 | General Electric Company | Impingement panel for a turbomachine |
US11994292B2 (en) | 2020-08-31 | 2024-05-28 | General Electric Company | Impingement cooling apparatus for 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)
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 |
-
2000
- 2000-06-16 IT IT2000MI001362A patent/IT1317978B1/it active
-
2001
- 2001-06-08 AU AU78443/01A patent/AU7844301A/en not_active Abandoned
- 2001-06-08 AT AT01956465T patent/ATE310896T1/de active
- 2001-06-08 WO PCT/EP2001/006484 patent/WO2001096712A1/en active IP Right Grant
- 2001-06-08 MX MXPA02012451A patent/MXPA02012451A/es unknown
- 2001-06-08 EP EP01956465A patent/EP1295014B1/en not_active Expired - Lifetime
- 2001-06-08 BR BR0111577-4A patent/BR0111577A/pt not_active Application Discontinuation
- 2001-06-08 RU RU2003101058/06A patent/RU2275554C2/ru not_active IP Right Cessation
- 2001-06-08 DE DE60115236T patent/DE60115236T2/de not_active Expired - Lifetime
- 2001-06-08 US US10/311,251 patent/US20030167776A1/en not_active Abandoned
- 2001-06-15 AR ARP010102872A patent/AR028133A1/es unknown
-
2002
- 2002-12-13 NO NO20025995A patent/NO330416B1/no not_active IP Right Cessation
Also Published As
Publication number | Publication date |
---|---|
DE60115236D1 (de) | 2005-12-29 |
AU7844301A (en) | 2001-12-24 |
US20030167776A1 (en) | 2003-09-11 |
NO20025995D0 (no) | 2002-12-13 |
EP1295014A1 (en) | 2003-03-26 |
AR028133A1 (es) | 2003-04-23 |
DE60115236T2 (de) | 2006-07-27 |
RU2275554C2 (ru) | 2006-04-27 |
IT1317978B1 (it) | 2003-07-21 |
ITMI20001362A1 (it) | 2001-12-16 |
NO330416B1 (no) | 2011-04-11 |
EP1295014B1 (en) | 2005-11-23 |
ATE310896T1 (de) | 2005-12-15 |
NO20025995L (no) | 2003-02-13 |
WO2001096712A1 (en) | 2001-12-20 |
MXPA02012451A (es) | 2003-04-25 |
ITMI20001362A0 (it) | 2000-06-16 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
B11A | Dismissal acc. art.33 of ipl - examination not requested within 36 months of filing | ||
B11Y | Definitive dismissal - extension of time limit for request of examination expired [chapter 11.1.1 patent gazette] |