DE102007025006A1 - Double shaft gas turbine, has bars arranged along circumference of bearing housing and extend via circular intermediate channel into space between outer circumference surface of housing and inner circumference surface of housing wall - Google Patents
Double shaft gas turbine, has bars arranged along circumference of bearing housing and extend via circular intermediate channel into space between outer circumference surface of housing and inner circumference surface of housing wall Download PDFInfo
- Publication number
- DE102007025006A1 DE102007025006A1 DE102007025006A DE102007025006A DE102007025006A1 DE 102007025006 A1 DE102007025006 A1 DE 102007025006A1 DE 102007025006 A DE102007025006 A DE 102007025006A DE 102007025006 A DE102007025006 A DE 102007025006A DE 102007025006 A1 DE102007025006 A1 DE 102007025006A1
- Authority
- DE
- Germany
- Prior art keywords
- intermediate channel
- housing
- pressure turbine
- struts
- strut
- 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.)
- Ceased
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
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Die Erfindung bezieht sich auf eine Gasturbine mit mehreren auf der gleichen Achse angeordneten Wellen.The The invention relates to a gas turbine with several on the same axis arranged waves.
Eine typische Gasturbine (nicht gezeigt) umfasst einen Kompressor, eine Brennkammer und eine Turbine. In der Gasturbine wird Luft durch den Kompressor komprimiert und der Brennkammer zugeführt, wo die komprimierte Luft mit Brennstoff, der separat zugeführt wird, vermischt wird, und das Gemisch aus komprimierter Luft und Brennstoffs verbrannt wird. Durch die Verbrennung wird Verbrennungsgas erzeugt und der Turbine zugeführt, in der Energie aus dem Verbrennungsgas extrahiert wird. Die Energie liefert eine Drehantriebskraft für den Kompressor und eine Antriebskraft, die bewirkt, dass ein Generator (nicht gezeigt) Elektrizität erzeugt. Nachdem die Drehantriebskraft von der Turbine erzeugt wurde, wird das Verbrennungsgas über einen Abgasdiffusor ausgestoßen.A Typical gas turbine (not shown) includes a compressor, a Combustion chamber and a turbine. In the gas turbine air is through the compressor is compressed and fed to the combustion chamber, where the compressed air with fuel supplied separately is mixed, and the mixture of compressed air and fuel is burned. The combustion generates combustion gas and fed to the turbine, in which energy is extracted from the combustion gas. The energy provides a rotational drive force for the compressor and a driving force that causes a generator (not shown) Electricity generated. After the rotary drive force was generated by the turbine, the combustion gas is over ejected an exhaust gas diffuser.
Die
Hochdruckturbine
Bei
der oben beschriebenen Doppelwellen-Gasturbine sind die Strebenabdeckungen
Da
außerdem
die Strebenabdeckungen
Entsprechend ist es eine Aufgabe der Erfindung, eine Doppelwellen-Gasturbine bereitzustellen, die klein ist und eine verbesserte Leistung bietet, wobei Strebenabdeckungen und Leitschaufeln der ersten Stufe wirksam integriert sind, um einen Druckverlust in einem Gasdurchgang sowie die Länge des Gasdurchgangs zu verringern.Corresponding It is an object of the invention, a double-shaft gas turbine which is small and offers improved performance, wherein strut covers and first stage vanes are effective are integrated to a pressure drop in a gas passage as well the length to reduce the gas passage.
Um die oben beschriebene Aufgabe zu erfüllen, umfasst eine Doppelwellen-Gasturbine gemäß der Erfindung die Merkmale des Patentanspruches 1. Diese Doppelwellen-Gasturbine umfasst eine Hochdruckturbine mit einem ringförmigen Gasdurchgangsauslass, eine Niederdruckturbine mit einem ringförmigen Gasdurchgangseinlass, einen ringförmigen Zwischenkanal, der den Gasdurchgangsauslass mit dem Gasdurchgangseinlass verbindet, ein Lager, das einen Rotor der Hochdruckturbine lagert und an einem Lagergehäuse angebracht ist, und mehrere Streben, die das Lagergehäuse haltern. Die Streben sind radial entlang dem Umfang des Lagergehäuses angeordnet und erstrecken sich durch den Zwischenkanal in einen Raum zwischen einer Außenumfangsfläche des Lagergehäuses und einer Innenumfangsfläche einer Gehäusewand, welche den Zwischenkanal umgibt. Der Zwischenkanal weist Strebenabdeckungen auf, durch die sich die Streben erstrecken und die als Leitschaufeln der ersten Stufe der Niederdruckturbine dienen.Around To accomplish the object described above comprises a double-shaft gas turbine according to the invention the features of claim 1. This twin-shaft gas turbine comprises a high-pressure turbine with an annular gas passage outlet, a low pressure turbine having an annular gas passage inlet, an annular Intermediate channel connecting the gas passage outlet to the gas passage inlet links, a bearing that supports a rotor of the high-pressure turbine and on a bearing housing is attached, and a plurality of struts that support the bearing housing. The struts are arranged radially along the circumference of the bearing housing and extend through the intermediate channel into a space between an outer peripheral surface of the bearing housing and an inner peripheral surface a housing wall, which surrounds the intermediate channel. The intermediate channel has strut covers through which the struts extend and which extend as vanes serve the first stage of the low-pressure turbine.
Der Zwischenkanal kann in mehrere Segmente entlang seinem Umfang unterteilt werden, wobei jedes Segment eine der Strebenabdeckungen aufweist, und die Streben können so vorgesehen sein, dass sie sich durch eine beliebige Anzahl der Strebenabdeckungen erstrecken.Of the Intermediate channel can be divided into several segments along its circumference with each segment having one of the strut covers, and the aspirations can be provided so that they pass through any number of strut covers extend.
Der Zwischenkanal kann in zwanzig Segmente unterteilt sein und die Streben können so vorgesehen sein, dass sie sich durch zehn der Strebenabdeckungen erstrecken, wobei die Strebenabdeckungen ohne die Streben sowie die Strebenabdeckungen mit den Streben alternierend angeordnet sind.Of the Intermediate channel can be divided into twenty segments and the struts can be provided so that they pass through ten of the strut covers extend, with the strut covers without the struts as well the strut covers are arranged alternately with the struts.
Jede Strebenabdeckung hat einen flügelförmigen Querschnitt, in dem die Breite eines Vorderabschnitts der Strebenabdeckung allmählich stromab in der Richtung der Gasströmung zunimmt.each Strut cover has a wing-shaped cross section, in which the width of a front portion of the strut cover gradually downstream in the direction of gas flow increases.
Im folgenden wird die Erfindung anhand bevorzugter Ausführungsformen unter Bezugnahme auf die beigefügten Zeichnungen näher erläutert, in denen zeigen:in the The following is the invention with reference to preferred embodiments with reference to the attached Drawings closer explains in which show:
Eine Doppelwellen-Gasturbine gemäß einer Ausführungsform der Erfindung wird im Detail nachstehend unter Bezugnahme auf die beigefügten Zeichnungen beschrieben.A Double shaft gas turbine according to one embodiment The invention will be described in detail below with reference to FIGS attached drawings described.
Wie
in
In
dieser Doppelwellen-Gasturbine wird Luft durch den Kompressor
Wie
in
Die
Hochdruckturbine
Die
Streben
Gemäß der Erfindung
funktionieren die Strebenabdeckungen
Genauer
gesagt, ist der Zwischenkanal
Jedes
Segment des Zwischenkanals
Wie
in
Die
Wie
oben beschrieben wurde, erfüllen
gemäß der vorliegenden
Ausführungsform
die Strebenabdeckungen
Daher
können
der Druckverlust in dem Gasdurchgang zwischen der Hochdruckturbine
Außerdem ist
gemäß der vorliegenden
Ausführungsform
der Zwischenkanal
Die
Erfindung ist nicht auf die oben beschriebene Ausführungsform
beschränkt.
Die Anzahl der Segmente, in die der Zwischenkanal
Claims (4)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US11/528,690 US20100303608A1 (en) | 2006-09-28 | 2006-09-28 | Two-shaft gas turbine |
US11/528,690 | 2006-09-28 |
Publications (1)
Publication Number | Publication Date |
---|---|
DE102007025006A1 true DE102007025006A1 (en) | 2008-04-10 |
Family
ID=39154786
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
DE102007025006A Ceased DE102007025006A1 (en) | 2006-09-28 | 2007-05-30 | Double shaft gas turbine, has bars arranged along circumference of bearing housing and extend via circular intermediate channel into space between outer circumference surface of housing and inner circumference surface of housing wall |
Country Status (4)
Country | Link |
---|---|
US (1) | US20100303608A1 (en) |
JP (1) | JP2008082323A (en) |
CN (1) | CN101153546B (en) |
DE (1) | DE102007025006A1 (en) |
Cited By (6)
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EP2192275A2 (en) | 2008-11-28 | 2010-06-02 | Pratt & Whitney Canada Corp. | Mid turbine frame system for gas turbine engine |
EP2192274A2 (en) * | 2008-11-28 | 2010-06-02 | Pratt & Whitney Canada Corp. | Mid turbine frame for gas turbine engine |
CN101963073B (en) * | 2009-07-22 | 2012-05-23 | 中国科学院工程热物理研究所 | Counterrotating turbine with overhung rotor blade structure |
EP2192270A3 (en) * | 2008-11-28 | 2012-12-26 | Pratt & Whitney Canada Corp. | Mid turbine frame system for gas turbine engine |
WO2020249887A1 (en) * | 2019-06-12 | 2020-12-17 | Safran Helicopter Engines | Annular component for supporting a turbine engine bearing |
US11396812B2 (en) | 2017-12-01 | 2022-07-26 | MTU Aero Engines AG | Flow channel for a turbomachine |
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DE102008062588B4 (en) | 2008-12-16 | 2010-11-25 | Siemens Aktiengesellschaft | Method for stabilizing the mains frequency of an electrical power network |
JP2011001950A (en) | 2009-05-19 | 2011-01-06 | Hitachi Ltd | Two-shaft gas turbine |
US9279341B2 (en) | 2011-09-22 | 2016-03-08 | Pratt & Whitney Canada Corp. | Air system architecture for a mid-turbine frame module |
US9458721B2 (en) * | 2011-09-28 | 2016-10-04 | United Technologies Corporation | Gas turbine engine tie rod retainer |
RU2647558C2 (en) * | 2012-01-09 | 2018-03-19 | Юнайтед Текнолоджиз Корпорейшн | Gas-turbine engine with gear transmission |
FR2986040B1 (en) * | 2012-01-20 | 2016-03-25 | Turbomeca | TURBOMACHINE BEARING SUPPORT |
WO2014105617A1 (en) * | 2012-12-29 | 2014-07-03 | United Technologies Corporation | Installation mounts for a turbine exhaust case |
US10240481B2 (en) * | 2012-12-29 | 2019-03-26 | United Technologies Corporation | Angled cut to direct radiative heat load |
DE112013006254T5 (en) * | 2012-12-29 | 2015-10-08 | Pw Power Systems, Inc. | Combination of flow divider and storage support |
US9631517B2 (en) | 2012-12-29 | 2017-04-25 | United Technologies Corporation | Multi-piece fairing for monolithic turbine exhaust case |
WO2014105688A1 (en) | 2012-12-31 | 2014-07-03 | United Technologies Corporation | Turbine exhaust case multi-piece frame |
US10054009B2 (en) | 2012-12-31 | 2018-08-21 | United Technologies Corporation | Turbine exhaust case multi-piece frame |
US9316153B2 (en) * | 2013-01-22 | 2016-04-19 | Siemens Energy, Inc. | Purge and cooling air for an exhaust section of a gas turbine assembly |
ES2948389T3 (en) | 2013-07-15 | 2023-09-11 | Raytheon Tech Corp | Turbine blades with variable joints |
EP3169878A1 (en) * | 2014-07-18 | 2017-05-24 | Siemens Energy, Inc. | Turbine assembly with detachable struts |
US10100676B2 (en) * | 2014-12-17 | 2018-10-16 | United Technologies Corporation | Intergrated seal supports |
US9771828B2 (en) | 2015-04-01 | 2017-09-26 | General Electric Company | Turbine exhaust frame and method of vane assembly |
US9784133B2 (en) * | 2015-04-01 | 2017-10-10 | General Electric Company | Turbine frame and airfoil for turbine frame |
US10273812B2 (en) | 2015-12-18 | 2019-04-30 | Pratt & Whitney Canada Corp. | Turbine rotor coolant supply system |
US11193385B2 (en) * | 2016-04-18 | 2021-12-07 | General Electric Company | Gas bearing seal |
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US10550726B2 (en) * | 2017-01-30 | 2020-02-04 | General Electric Company | Turbine spider frame with additive core |
US11401835B2 (en) * | 2017-06-12 | 2022-08-02 | General Electric Company | Turbine center frame |
JP2021127755A (en) * | 2020-02-17 | 2021-09-02 | 三菱重工業株式会社 | Two-shaft gas turbine |
JP7352590B2 (en) | 2021-04-02 | 2023-09-28 | 三菱重工業株式会社 | gas turbine |
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US4478551A (en) * | 1981-12-08 | 1984-10-23 | United Technologies Corporation | Turbine exhaust case design |
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CN1167207A (en) * | 1997-02-03 | 1997-12-10 | 周展开 | Inverse (main shaft) combustion chamber type double-shaft gas turbine |
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US7063505B2 (en) * | 2003-02-07 | 2006-06-20 | General Electric Company | Gas turbine engine frame having struts connected to rings with morse pins |
US6983608B2 (en) * | 2003-12-22 | 2006-01-10 | General Electric Company | Methods and apparatus for assembling gas turbine engines |
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-
2006
- 2006-09-28 US US11/528,690 patent/US20100303608A1/en not_active Abandoned
-
2007
- 2007-05-15 JP JP2007128757A patent/JP2008082323A/en active Pending
- 2007-05-30 DE DE102007025006A patent/DE102007025006A1/en not_active Ceased
- 2007-05-31 CN CN2007101088359A patent/CN101153546B/en not_active Expired - Fee Related
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2192275A2 (en) | 2008-11-28 | 2010-06-02 | Pratt & Whitney Canada Corp. | Mid turbine frame system for gas turbine engine |
EP2192274A2 (en) * | 2008-11-28 | 2010-06-02 | Pratt & Whitney Canada Corp. | Mid turbine frame for gas turbine engine |
EP2192274A3 (en) * | 2008-11-28 | 2012-12-26 | Pratt & Whitney Canada Corp. | Mid turbine frame for gas turbine engine |
EP2192270A3 (en) * | 2008-11-28 | 2012-12-26 | Pratt & Whitney Canada Corp. | Mid turbine frame system for gas turbine engine |
EP2192275A3 (en) * | 2008-11-28 | 2013-01-02 | Pratt & Whitney Canada Corp. | Mid turbine frame system for gas turbine engine |
CN101963073B (en) * | 2009-07-22 | 2012-05-23 | 中国科学院工程热物理研究所 | Counterrotating turbine with overhung rotor blade structure |
US11396812B2 (en) | 2017-12-01 | 2022-07-26 | MTU Aero Engines AG | Flow channel for a turbomachine |
WO2020249887A1 (en) * | 2019-06-12 | 2020-12-17 | Safran Helicopter Engines | Annular component for supporting a turbine engine bearing |
FR3097259A1 (en) * | 2019-06-12 | 2020-12-18 | Safran Helicopter Engines | ANNULAR SUPPORT PART OF A BEARING FOR A TURBOMACHINE |
US11982198B2 (en) | 2019-06-12 | 2024-05-14 | Safran Helicopter Engines | Annular component for supporting a turbine engine bearing |
Also Published As
Publication number | Publication date |
---|---|
CN101153546A (en) | 2008-04-02 |
US20100303608A1 (en) | 2010-12-02 |
JP2008082323A (en) | 2008-04-10 |
CN101153546B (en) | 2010-06-16 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
OP8 | Request for examination as to paragraph 44 patent law | ||
R016 | Response to examination communication | ||
R002 | Refusal decision in examination/registration proceedings | ||
R003 | Refusal decision now final |
Effective date: 20130625 |