CN101153546B - Doppelwellen-gasturbine - Google Patents
Doppelwellen-gasturbine Download PDFInfo
- Publication number
- CN101153546B CN101153546B CN2007101088359A CN200710108835A CN101153546B CN 101153546 B CN101153546 B CN 101153546B CN 2007101088359 A CN2007101088359 A CN 2007101088359A CN 200710108835 A CN200710108835 A CN 200710108835A CN 101153546 B CN101153546 B CN 101153546B
- Authority
- CN
- China
- Prior art keywords
- pillar
- pressure turbine
- lid
- intermediate conduit
- doppelwellen
- 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.)
- Expired - Fee Related
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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
A double axle gas turbine comprises: a high pressure turbine with a circular air duct outlet; a low pressure turbine with a circular air duct inlet; a circular middle pipe connecting the air duct outlet to the air duct inlet; a bearing supporting the rotor of the high pressure turbine and connected to the bearing case; a plurality of posts supporting the bearing case. The posts are radially arranged along the circumference of the bearing case so as to run through the middle pipe between the peripheral surface and the inner circumferential surface of the case wall around the middle pipe. The middle pipe has a post cover. The posts runs through the covers and the post covers are used as the first level stator vane of the low pressure turbine.
Description
Technical field
The present invention relates to a kind of gas turbine, this gas turbine comprises many axles that are arranged on the same axis.
Background technique
Typical gas turbine (not shown) comprises compressor, firing chamber and turbine.In gas turbine, air is by compressor compresses and be fed to the firing chamber, and pressurized air mixes with independent supplied fuel and the mixture of burn this pressurized air and fuel in this firing chamber.Produce combustion gas by burning, and these combustion gas are fed to turbine, draw the energy of these combustion gas at this turbine place.Energy applies rotary driving force that is used for compressor and the driving force that is used to make the generating of generator (not shown).After turbine produced rotary driving force, combustion gas were discharged by exhaust diffuser.
Fig. 7 illustrates the example as the Doppelwellen-gasturbine of the common general knowledge of the gas turbine of air breathing engine derivation.This gas turbine comprises: high-pressure turbine 100, this high-pressure turbine 100 have ring-type gas channel outlet 101; Low-pressure turbine 102, this low-pressure turbine 102 have ring-type gas channel inlet 103; Ring-type intermediate conduit 104, this ring-type intermediate conduit 104 is connected to gas channel inlet 103 with gas channel outlet 101; Shaft bearing 105, this shaft bearing 105 supports the rotor of high-pressure turbine 100; With a plurality of pillars 108, these a plurality of pillar 108 back shaft journal bearings 105.Pillar 108 arranges and runs through pillar lid 107 along the peripheral radial of shaft bearing 105, and these pillars lids 107 are integral with intermediate conduit 104 at the outer surface of shaft bearing 105 with in the space between the interior perimeter surface of the shell wall 106 of intermediate conduit 104.
High-pressure turbine 100 is as gas generator, this gas generator produces and is used for the high temperature of Driven Compressor (not shown), the combustion gas of high pressure, and low-pressure turbine 102 is used as power turbine, and this power turbine drives the load (not shown) of generator or homologue with harvest energy.In Fig. 7, reference character 109 and 110 is represented the first order stator vane and the first order rotor blade of low-pressure turbine 102 respectively.
In above-mentioned Doppelwellen-gasturbine, be used for pillar lid 107 gas channels that are arranged between high-pressure turbine 100 and the low-pressure turbine 102 that prevent that pillar 108 from being heated by high-temperature gas.Therefore, cause aerodynamic losses along the pillar of the air-flow setting that is used for first order rotor blade 110 lid 107 and first order stator vane 109 at gas channel.
In addition, because pillar lid 107 and first order stator vane 109 arrange in tandem, promptly arrange, so the length of increase gas channel along the direction of air-flow.Therefore, also increase the length of low-pressure turbine 102 along rotor shaft, this will cause the increase of gas turbine sizes.
Summary of the invention
Therefore, the purpose of this invention is to provide a kind of little and the Doppelwellen-gasturbine that improves performance is provided, its B-C post lid and first order stator vane by combination effectively to reduce the pressure loss in the gas channel and the length of gas channel.
To achieve these goals, Doppelwellen-gasturbine according to the present invention comprises: high-pressure turbine, this high-pressure turbine have the annular gas passage outlet; Low-pressure turbine, this low-pressure turbine have the annular gas passage inlet; The annular intermediate conduit, this annular intermediate conduit is connected to the gas channel inlet with the gas channel outlet; Bearing, the rotor of this bearings high-pressure turbine also is coupled to cartridge housing; With a plurality of pillars, this cartridge housing of these shore supports.Pillar arranges along the peripheral radial of cartridge housing, and runs through intermediate conduit at the outer surface of cartridge housing with in the space between the interior perimeter surface of the shell wall of intermediate conduit.Intermediate conduit has the pillar lid, and pillar runs through these pillar lids, and the pillar lid is as the first order stator vane of low-pressure turbine.
Intermediate conduit can be divided into a plurality of sections along its periphery, every section pillar lid that has in the pillar lid, and pillar can be arranged to run through the pillar lid of any amount.
Intermediate conduit can be divided into 20 sections, and pillar can be arranged to run through ten pillars lids in the pillar lid, and the pillar lid that does not have the pillar lid of pillar and have a pillar is alternately arranged.
Each pillar lid has the wing cross section, and in this wing cross section, the width of the front portion of pillar lid increases gradually along the trip that is directed downwards of air-flow.
Description of drawings
Fig. 1 is the sectional view according to the major component of the Doppelwellen-gasturbine of the embodiment of the invention;
Fig. 2 A is the sectional view of intermediate conduit;
Fig. 2 B is the perspective cut-away schematic view of intermediate conduit;
Fig. 3 A is the view sub-anatomy of intermediate conduit;
Fig. 3 B is the exploded perspective sectional view of intermediate conduit;
Fig. 4 A is the view sub-anatomy that is in the intermediate conduit of another state;
Fig. 4 B is the exploded perspective sectional view that is in the intermediate conduit of another state;
Fig. 5 is the schematic diagram that the general structure of Doppelwellen-gasturbine is shown;
Fig. 6 is the sectional view of Fig. 1 of VI-VI gained along the line; And
Fig. 7 is the sectional view of the critical piece of known Doppelwellen-gasturbine.
Embodiment
Below with reference to accompanying drawing, describe Doppelwellen-gasturbine in detail according to the embodiment of the invention.
As shown in Figure 5, the Doppelwellen-gasturbine according to present embodiment comprises: compressor 10; Firing chamber 11; High-pressure turbine 12, this high-pressure turbine 12 is as gas generator; With low-pressure turbine 13, this low-pressure turbine 13 is as power turbine.
In this Doppelwellen-gasturbine, air is by compressor 10 compression and be fed to firing chamber 11, and pressurized air mixes with independent supplied fuel and the mixture of burn this pressurized air and fuel in firing chamber 11.Produce combustion gas by burning, and these combustion gas are fed to high-pressure turbine 12 and low-pressure turbine 13.High-pressure turbine 12 produces and for example is used for 5, the high temperature of the speed driving compressor 10 of 000rpm, the combustion gas of high pressure, and low-pressure turbine 13 is with for example 3, the speed driving generator 14 of 000rpm is to collect the energy of combustion gas.
Shown in Fig. 1,2A and 2B, high-pressure turbine 12 and low-pressure turbine 13 have annular gas passage outlet 15 and annular gas passage inlet 16 respectively, and this annular gas passage outlet 15 and annular gas passage inlet 16 utilize annular intermediate conduit 17 to be connected to each other.The bearing 19 that supports the rotor 18 of high-pressure turbine 12 is connected to the cartridge housing 20 that is supported by a plurality of pillars 23.Pillar 23 arranges and runs through pillar lid 22 along the peripheral radial of cartridge housing 20, and these pillars lids 22 are integral with intermediate conduit 17 at the outer surface of cartridge housing 20 with in the space between the interior perimeter surface of the middle shell wall 21 of intermediate conduit 17.
High-pressure turbine 12 has gas channel, and in this gas channel, stator vane 25 is supported so that be arranged in two levels by inner shell wall 24A, and the position of rotor blade 26 between two levels of stator vane 25 supported by rotor 18.The outside shell wall 24B of high-pressure turbine 12 by bolt to middle shell wall 21.Low-pressure turbine 13 has gas channel, in this gas channel, by the stator vane 28 of inner wall 27A support and rotor blade 29 arranged alternate in a plurality of levels that is supported by the rotor (not shown).The casing wall 27B of low-pressure turbine 13 is also by shell wall 21 in the middle of the bolt.
According to present embodiment, the pillar of the intermediate conduit 17 that pillar 23 runs through lid 22 is as the first order stator vane in the low-pressure turbine 13.Therefore, although in known configurations, first order stator vane is arranged in the gas channel inlet of low-pressure turbine, and first order rotor blade 29 is set directly in the present embodiment.
More specifically, intermediate conduit 17 is divided into for example 20 sections along its periphery, and every section covers 22 with single pillar and is integral.In pillar lid 22, pillar 23 is arranged to run through for example ten pillar lids 22.In other words, pillar 23 is provided with every a pillar lid 22.
Coupling 32a and 32b that every section place, end utilization within it of intermediate conduit 17 is arranged on are therebetween supported by cartridge housing 20, and utilize the supporting element 33a and the 33b that are arranged on therebetween to be supported by middle shell wall 21 at its place, outer end.In Fig. 1, utilize the link 34 that is arranged on therebetween to support by middle shell wall 21 indirectly along the upstream holder 33a of airflow direction.
As shown in Figure 6, each pillar lid 22 has the wing cross section, and in this wing cross section, the width of the front portion of pillar lid 22 increases gradually along the trip that is directed downwards of air-flow.Therefore, pillar lid 22 allows gases reposefully along the Surface runoff of pillar lid 22, and can not produce shock wave, thereby provides function as nozzle vane effectively for the first order rotor blade 29 in the low-pressure turbine 13.
Fig. 3 A illustrates the state that middle shell wall 21 separates with the structure shown in the 2B from Fig. 2 A respectively with 3B.Fig. 4 A and 4B illustrate the state that pillar 23 is extracted from the structure shown in Fig. 3 A and the 3B respectively.Can understand the process of the section of assembling Doppelwellen-gasturbine or replacing pillar 23 and/or intermediate conduit 17 by Fig. 4 A and 4B.
As mentioned above, according to present embodiment, the pillar of intermediate conduit 17 lid 22 is as the function of the first order stator vane (nozzle vane) of low-pressure turbine 13.Therefore, be different from known structure, needn't in the gas channel inlet 16 of low-pressure turbine 13, provide first order stator vane (nozzle vane), and can directly arrange rotor blade 29.
Therefore, can reduce the pressure loss in the gas channel between high-pressure turbine 12 and the low-pressure turbine 13 and the length of the gas channel in the low-pressure turbine 13.Therefore, can improve turbine performance simultaneously and reduce size.
In addition, according to present embodiment, intermediate conduit 17 is divided into a plurality of sections along its periphery, and every section covers 22 with single pillar and combines.In addition, pillar 23 can be arranged to run through the pillar lid 22 of any amount.Therefore, can change the quantity of pillar to be installed 23 as required.In addition, can easily change the section of pillar 23 and intermediate conduit 17.
The present invention is not limited to the foregoing description.Certainly, various kinds ground changes the quantity of the quantity of the section that intermediate conduit 17 is divided into, pillar 23 to be installed, the sectional shape of each pillar lid 22 etc. within the scope of the invention.
Claims (4)
1. Doppelwellen-gasturbine comprises:
High-pressure turbine, this high-pressure turbine have the outlet of ring-type gas channel;
Low-pressure turbine, this low-pressure turbine have ring-type gas channel inlet;
The ring-type intermediate conduit, this ring-type intermediate conduit is connected to described gas channel inlet with described gas channel outlet;
Bearing, the rotor of the described high-pressure turbine of this bearings also is coupled to cartridge housing; With
A plurality of pillars, this cartridge housing of these shore supports, described pillar are along the outer surface radial arrangement of described cartridge housing, and run through described intermediate conduit at the outer surface of described cartridge housing with in the space between the interior perimeter surface of the shell wall of described intermediate conduit,
Wherein, described intermediate conduit has the pillar lid, and described pillar runs through these pillar lids, and described pillar lid is as the first order stator vane of described low-pressure turbine.
2. Doppelwellen-gasturbine as claimed in claim 1, wherein, described intermediate conduit is divided into a plurality of sections along perimeter surface in the tool, and each section has a pillar lid in the described pillar lid, and
Wherein each the pillar lid in the described pillar lid of any amount is arranged to be run through by a corresponding described pillar.
3. Doppelwellen-gasturbine as claimed in claim 2, wherein, described intermediate conduit is divided into 20 sections, and described pillar is arranged to run through ten pillars lids in the described pillar lid, and the described pillar lid that does not have the described pillar lid of described pillar and have a described pillar is alternately arranged.
4. Doppelwellen-gasturbine as claimed in claim 1, wherein, each pillar lid has wing cross section, and in this wing cross section, the width with respect to the front portion of airflow direction of described pillar lid increases downstream gradually along airflow direction.
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 (2)
| Publication Number | Publication Date |
|---|---|
| CN101153546A CN101153546A (en) | 2008-04-02 |
| CN101153546B true CN101153546B (en) | 2010-06-16 |
Family
ID=39154786
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2007101088359A Expired - Fee Related CN101153546B (en) | 2006-09-28 | 2007-05-31 | Doppelwellen-gasturbine |
Country Status (4)
| Country | Link |
|---|---|
| US (1) | US20100303608A1 (en) |
| JP (1) | JP2008082323A (en) |
| CN (1) | CN101153546B (en) |
| DE (1) | DE102007025006A1 (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US20100132371A1 (en) * | 2008-11-28 | 2010-06-03 | Pratt & Whitney Canada Corp. | Mid turbine frame system for gas turbine engine |
| US8347500B2 (en) * | 2008-11-28 | 2013-01-08 | Pratt & Whitney Canada Corp. | Method of assembly and disassembly of a gas turbine mid turbine frame |
| US8061969B2 (en) | 2008-11-28 | 2011-11-22 | Pratt & Whitney Canada Corp. | Mid turbine frame system for gas turbine engine |
| 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 |
| 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 |
| 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 |
| EP2802745A4 (en) * | 2012-01-09 | 2015-10-21 | United Technologies Corp | Gas turbine engine with geared architecture |
| FR2986040B1 (en) * | 2012-01-20 | 2016-03-25 | Turbomeca | TURBOMACHINE BEARING SUPPORT |
| US9631517B2 (en) | 2012-12-29 | 2017-04-25 | United Technologies Corporation | Multi-piece fairing for monolithic turbine exhaust case |
| US10240481B2 (en) * | 2012-12-29 | 2019-03-26 | United Technologies Corporation | Angled cut to direct radiative heat load |
| WO2014105572A1 (en) * | 2012-12-29 | 2014-07-03 | United Technologies Corporation | Combination flow divider and bearing support |
| US10036324B2 (en) * | 2012-12-29 | 2018-07-31 | United Technologies Corporation | Installation mounts for a turbine exhaust case |
| US9890663B2 (en) | 2012-12-31 | 2018-02-13 | United Technologies Corporation | Turbine exhaust case multi-piece frame |
| JP6232446B2 (en) * | 2012-12-31 | 2017-11-15 | ユナイテッド テクノロジーズ コーポレイションＵｎｉｔｅｄ Ｔｅｃｈｎｏｌｏｇｉｅｓ Ｃｏｒｐｏｒａｔｉｏｎ | Multi-piece frame for turbine exhaust case |
| US9316153B2 (en) * | 2013-01-22 | 2016-04-19 | Siemens Energy, Inc. | Purge and cooling air for an exhaust section of a gas turbine assembly |
| JP6126745B2 (en) * | 2013-07-15 | 2017-05-10 | ユナイテッド テクノロジーズ コーポレイションＵｎｉｔｅｄ Ｔｅｃｈｎｏｌｏｇｉｅｓ Ｃｏｒｐｏｒａｔｉｏｎ | Turbine vane with variable fillet |
| JP2017525883A (en) | 2014-07-18 | 2017-09-07 | シーメンス エナジー インコーポレイテッド | Turbine assembly with removable struts |
| EP3040523B1 (en) * | 2014-12-17 | 2018-02-07 | United Technologies Corporation | Integrated seal supports |
| US9784133B2 (en) | 2015-04-01 | 2017-10-10 | General Electric Company | Turbine frame and airfoil for turbine frame |
| US9771828B2 (en) | 2015-04-01 | 2017-09-26 | General Electric Company | Turbine exhaust frame and method of vane assembly |
| 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 |
| FR3055655B1 (en) * | 2016-09-06 | 2019-04-05 | Safran Aircraft Engines | INTERMEDIATE CASE OF TURBOMACHINE TURBINE |
| 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 |
| DE102017221684A1 (en) | 2017-12-01 | 2019-06-06 | MTU Aero Engines AG | Turbomachinery flow channel |
| FR3097259B1 (en) * | 2019-06-12 | 2021-05-21 | Safran Helicopter Engines | ANNULAR PART OF A BEARING SUPPORT FOR A TURBOMACHINE |
| 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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| CN1769648A (en) * | 2004-11-04 | 2006-05-10 | 通用电气公司 | 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
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| US4304522A (en) * | 1980-01-15 | 1981-12-08 | Pratt & Whitney Aircraft Of Canada Limited | Turbine bearing support |
| US4965994A (en) * | 1988-12-16 | 1990-10-30 | General Electric Company | Jet engine turbine support |
| CN1167207A (en) * | 1997-02-03 | 1997-12-10 | 周展开 | Inverse setting (spindle setting) combustion chamber type double-axle gas-turbine |
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| JP特开2001-123804A 2001.05.08 |
Also Published As
| Publication number | Publication date |
|---|---|
| DE102007025006A1 (en) | 2008-04-10 |
| US20100303608A1 (en) | 2010-12-02 |
| JP2008082323A (en) | 2008-04-10 |
| CN101153546A (en) | 2008-04-02 |
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Owner name: MITSUBISHI HITACHI POWER SYSTEM LTD. Free format text: FORMER OWNER: MITSUBISHI JUKOGIO KK Effective date: 20150407 |
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Effective date of registration: 20150407 Address after: yokohama Patentee after: Mitsubishi Hitachi Power System Ltd. Address before: Tokyo, Japan Patentee before: Mit-subishi Heavy Industries Ltd. |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20100616 Termination date: 20210531 |