EP2028344A1 - Conduit de transition - Google Patents
Conduit de transition Download PDFInfo
- Publication number
- EP2028344A1 EP2028344A1 EP07016387A EP07016387A EP2028344A1 EP 2028344 A1 EP2028344 A1 EP 2028344A1 EP 07016387 A EP07016387 A EP 07016387A EP 07016387 A EP07016387 A EP 07016387A EP 2028344 A1 EP2028344 A1 EP 2028344A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- transition duct
- low pressure
- pressure region
- vane
- generating element
- 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.)
- Withdrawn
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
-
- 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
- F05D2230/90—Coating; Surface treatment
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
-
- 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
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/12—Fluid guiding means, e.g. vanes
- F05D2240/127—Vortex generators, turbulators, or the like, for mixing
-
- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
-
- 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
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
Definitions
- the low pressure region generating element may extend from an upper wall or from a bottom wall of the transition duct, preferably at the outlet of the transition duct.
- the low pressure region generating element may extend from the upper wall to the bottom wall. This allows a stable mounting of the low pressure region generating element inside of the transition duct especially if the low pressure region generating element is fixed to the upper wall as well as to the bottom wall of the transition duct.
- the used low pressure region generating element can be located in the transition duct such that the centreline of the low pressure region generating element is perpendicular to the centreline of the transition duct.
- the transition duct 1 as it is shown in Figure 3 , comprises an upper wall 10 and a bottom wall 11.
- the vane 7 is mounted at the centre of the outlet 5 of the transition duct 1 and is, in the present embodiment, fixed to the upper wall 10 and also to the bottom wall 11. If the vane 7 is at both its ends fixed (perpendicular) to the transition duct 1 it should have sufficient strength not to experience a condition of collapse due to the heating of the centre part of the vane 7. Whether this happens depends on the strength of the vane 7 itself relative to the structural strength of the walls in the transition duct 1.
- FIG 4 the vane 7 is shown in a perspective view.
- the figure shows the vane 7 with its internal hollow space 8 and the opening 14.
- the centreline 3 of the vane 7 may be perpendicular to the centreline 2 of the transition duct 1 when the vane 7 is mounted in the transition duct 1.
- a suitable bond coat would be a so-called MCrAlX coating, where M stand for iron (Fe), cobalt (Co) or nickel (Ni) and X for yttrium (Y) and/or silicon (Si) and/or at least one rare earth element and/or hafnium (Hf).
- M stand for iron (Fe), cobalt (Co) or nickel (Ni)
- X for yttrium (Y) and/or silicon (Si) and/or at least one rare earth element and/or hafnium (Hf).
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP07016387A EP2028344A1 (fr) | 2007-08-21 | 2007-08-21 | Conduit de transition |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP07016387A EP2028344A1 (fr) | 2007-08-21 | 2007-08-21 | Conduit de transition |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2028344A1 true EP2028344A1 (fr) | 2009-02-25 |
Family
ID=39135224
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP07016387A Withdrawn EP2028344A1 (fr) | 2007-08-21 | 2007-08-21 | Conduit de transition |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP2028344A1 (fr) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2738355A1 (fr) * | 2012-11-30 | 2014-06-04 | General Electric Company | Système de moteur à turbine à gaz et procédé associé |
WO2014099074A3 (fr) * | 2012-09-26 | 2014-08-21 | United Technologies Corporation | Chambre de combustion de moteur à turbine à gaz ayant une pale de chambre de combustion intégrée |
CN104235879A (zh) * | 2014-08-08 | 2014-12-24 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | 燃气轮机燃烧室过渡段结构 |
US9783309B2 (en) | 2013-07-16 | 2017-10-10 | The Boeing Company | Methods and device for mixing airflows in environmental control systems |
WO2018167913A1 (fr) * | 2017-03-16 | 2018-09-20 | 株式会社 東芝 | Raccord de réduction |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3652181A (en) * | 1970-11-23 | 1972-03-28 | Carl F Wilhelm Jr | Cooling sleeve for gas turbine combustor transition member |
US3930748A (en) * | 1972-08-02 | 1976-01-06 | Rolls-Royce (1971) Limited | Hollow cooled vane or blade for a gas turbine engine |
US4719748A (en) * | 1985-05-14 | 1988-01-19 | General Electric Company | Impingement cooled transition duct |
JPH01155120A (ja) * | 1987-12-11 | 1989-06-19 | Hitachi Ltd | ガスタービン燃焼器の尾筒 |
US5397216A (en) * | 1992-10-26 | 1995-03-14 | Asea Brown Boveri Ltd. | Flow divider for radial-axial inlet housings |
US20050084657A1 (en) * | 2002-08-02 | 2005-04-21 | Minoru Ohara | Method for forming heat shielding film, masking pin and tail pipe of combustor |
-
2007
- 2007-08-21 EP EP07016387A patent/EP2028344A1/fr not_active Withdrawn
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3652181A (en) * | 1970-11-23 | 1972-03-28 | Carl F Wilhelm Jr | Cooling sleeve for gas turbine combustor transition member |
US3930748A (en) * | 1972-08-02 | 1976-01-06 | Rolls-Royce (1971) Limited | Hollow cooled vane or blade for a gas turbine engine |
US4719748A (en) * | 1985-05-14 | 1988-01-19 | General Electric Company | Impingement cooled transition duct |
JPH01155120A (ja) * | 1987-12-11 | 1989-06-19 | Hitachi Ltd | ガスタービン燃焼器の尾筒 |
US5397216A (en) * | 1992-10-26 | 1995-03-14 | Asea Brown Boveri Ltd. | Flow divider for radial-axial inlet housings |
US20050084657A1 (en) * | 2002-08-02 | 2005-04-21 | Minoru Ohara | Method for forming heat shielding film, masking pin and tail pipe of combustor |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014099074A3 (fr) * | 2012-09-26 | 2014-08-21 | United Technologies Corporation | Chambre de combustion de moteur à turbine à gaz ayant une pale de chambre de combustion intégrée |
US9482432B2 (en) | 2012-09-26 | 2016-11-01 | United Technologies Corporation | Gas turbine engine combustor with integrated combustor vane having swirler |
EP2738355A1 (fr) * | 2012-11-30 | 2014-06-04 | General Electric Company | Système de moteur à turbine à gaz et procédé associé |
CN103850796A (zh) * | 2012-11-30 | 2014-06-11 | 通用电气公司 | 燃气涡轮发动机系统及其相关方法 |
US9551492B2 (en) | 2012-11-30 | 2017-01-24 | General Electric Company | Gas turbine engine system and an associated method thereof |
US9783309B2 (en) | 2013-07-16 | 2017-10-10 | The Boeing Company | Methods and device for mixing airflows in environmental control systems |
CN104235879A (zh) * | 2014-08-08 | 2014-12-24 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | 燃气轮机燃烧室过渡段结构 |
WO2018167913A1 (fr) * | 2017-03-16 | 2018-09-20 | 株式会社 東芝 | Raccord de réduction |
US11098600B2 (en) | 2017-03-16 | 2021-08-24 | Toshiba Energy Systems & Solutions Corporation | Transition piece |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US10995954B2 (en) | Gas turbine engine with igniter stack or borescope mount having noncollinear cooling passages | |
JP5178207B2 (ja) | 翼形、スリーブ及び燃焼器アセンブリの組立方法 | |
EP2587157B1 (fr) | Système et procédé de réduction des oscillations dynamiques de combustion et de NOx dans une chambre de combustion | |
EP1794503B1 (fr) | Chambre de combustion sans bouclier thermique | |
EP2541146B1 (fr) | Ensemble de chambre de combustion de turbomachine comportant un système de modification de vortex | |
EP3018416B1 (fr) | Paroi flottante refroidie par film et par impact avec agencements sur sa face arrière | |
EP3115695A2 (fr) | Dôme conique plat étanche des chambres de combustion de moteur de vol | |
EP3330612B1 (fr) | Systèmes et procédés pour panneau de chambre de combustion | |
EP2584266B1 (fr) | Chambre de combustion et procédé de conditionnement d'écoulement à travers une chambre de combustion | |
EP3048371B1 (fr) | Contrôle de transfert thermique passif à trou de dilution de dispositif de combustion | |
EP3047128B1 (fr) | Variation contrôlée de la chute de pression par refroidissement par effusion dans une chambre de combustion à double paroi d'une turbine à gaz | |
EP2691610B1 (fr) | Ouïe de refroidissement de système de combustion de turbine | |
EP3748126B1 (fr) | Composants pour moteurs à turbine à gaz | |
EP3026343B1 (fr) | Structure d'orifice auto-refroidi | |
EP3205816A1 (fr) | Trous de refroidissement par impact pour un composant de moteur à turbine | |
EP2028344A1 (fr) | Conduit de transition | |
EP3315866A1 (fr) | Ensemble de chambre de combustion comportant un composant auxiliaire monté | |
CN107143382B (zh) | 用于先进膜冷却的具有小复杂特征的cmc制品 | |
KR20190041933A (ko) | 가스 터빈 천이부 부품을 위한 후방 프레임 조립체 | |
EP2613089B1 (fr) | Chambre de combustion et procédé de distribution de carburant dans la chambre de combustion | |
EP2246627A2 (fr) | Entrée d'air avec déflecteur pour système de combustion | |
US8157525B2 (en) | Methods and apparatus relating to turbine airfoil cooling apertures | |
US20190249875A1 (en) | Liner for a Gas Turbine Engine Combustor | |
WO2019002274A1 (fr) | Composant de turbomachine et procédé de fabrication du composant de turbomachine | |
EP3321584A1 (fr) | Panneau de chemise de chambre de combustion axialement non plane pour chambre de combustion de turbine à gaz |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR |
|
AX | Request for extension of the european patent |
Extension state: AL BA HR MK RS |
|
AKX | Designation fees paid | ||
REG | Reference to a national code |
Ref country code: DE Ref legal event code: 8566 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 20090826 |