CN1134505A - 被冷却的壁部件 - Google Patents
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- CN1134505A CN1134505A CN95119048A CN95119048A CN1134505A CN 1134505 A CN1134505 A CN 1134505A CN 95119048 A CN95119048 A CN 95119048A CN 95119048 A CN95119048 A CN 95119048A CN 1134505 A CN1134505 A CN 1134505A
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- 238000001816 cooling Methods 0.000 claims abstract description 80
- 238000010304 firing Methods 0.000 claims description 18
- 210000005239 tubule Anatomy 0.000 claims description 18
- 239000002826 coolant Substances 0.000 abstract description 10
- 238000009413 insulation Methods 0.000 description 6
- 238000002485 combustion reaction Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 4
- 230000001154 acute effect Effects 0.000 description 2
- 230000002349 favourable effect Effects 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 210000004072 lung Anatomy 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005204 segregation Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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- 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
- F23R3/005—Combined with pressure or heat exchangers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/82—Jet pipe walls, e.g. liners
- F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
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- 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
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- 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
- F23R2900/03041—Effusion cooled combustion chamber walls or domes
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S165/00—Heat exchange
- Y10S165/908—Fluid jets
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Gas Burners (AREA)
- Shaping By String And By Release Of Stress In Plastics And The Like (AREA)
- Heating, Cooling, Or Curing Plastics Or The Like In General (AREA)
Abstract
在一种带有多个靠近内壁(1)并与其平行伸展的分隔开的对流冷却的纵向冷却通道(2)的被冷却壁部件,相邻的纵向冷却通道分别通过中间肋(3)相连,在纵向冷却通道的下游端设有与至少一个靠近壁部件的外壁(5)设置的回流冷却通道(6)相连的转向装置(4),从该回流冷却通道分支出多个朝被冷却壁部件的内壁伸展并设在中间肋内的细管(7)。采用这种壁部件,冷却介质可以被多次利用来进行冷却(对流冷却、喷射冷却、薄膜冷却)。
Description
本发明涉及一种被冷却的壁部件,例如一种诸如燃烧室壁的环流式热涡轮机组成件的壁部件。
采用对流式冷却方法来冷却燃烧室壁以避免太高的材料温度是公知技术,在这种冷却方法中,冷却介质以跟燃烧室流成顺流或逆流的原理在一条位于燃烧室内壁与燃烧室外壁之间的冷却通道内流动,同时吸收热量,该冷却通道可以是一个环形槽道或者是相互分隔开的分立的冷却通道。这种对流式冷却方法可以跟冲击式冷却(Prallkülung)结合来产生高的传热系数(DE 28 36 539 C2)。
此外,将空气有控制地导入燃烧区内来冷却燃烧室壁的冷却技术是公知的。这适用于例如薄膜冷却,在这种冷却方式中冷却介质穿过在燃烧室内壁上的开孔进入燃烧室内部,沿着燃烧室壁的内侧流动并在那里形成一层构成一层绝热层并降低壁的热负荷的薄膜。
这些公知的冷却技术几乎不再能够满足在燃气轮机设备的效率方面、在与此相连的极高的温度方面以及尽可能低的冷却空气消耗方面的日益提高的要求。
本发明力图避免这些缺点。因此本发明的目的在于提供一种冷却介质在其内被多次利用来进行冷却从而提高了冷却效率的被冷却壁部件。
本发明的目的可通过下述的技术方案得以实现。一种被冷却的壁部件,它带有多个靠近内壁并与其平行地伸展的分隔开的对流冷却的纵向冷却通道,其中相邻的纵向冷却通道分别通过中间肋相连,在纵向冷却通道的下游端设有转向装置,该转向装置与至少一个靠近壁部件的外壁设置的回流冷却通道相连,从该回流冷却通道分支出多个朝向被冷却的壁部件的内壁伸展并设置在中间肋中的细管。
本发明的优点在于,冷却介质、例如冷却空气,被多次利用,一次是用于在纵向冷却通道内进行对流冷却,接着是用于在横向伸展的细管内进行对流冷却,后一个冷却呈现成喷射冷却(气体通过小开孔),最后用于对被冷却的壁部件进行薄膜冷却。
如果细管跟回流冷却通道内的流向成直角来设置,将是特别有利的。
此外,如果细管跟回流冷却通道内的流向成一个偏离于直角的角度、例如一个锐角来设置在中间肋内,也可能是有利的。
再者,如果壁部件是一个燃烧室冷却衬瓦(Brennkammerkühl-ziegel)并且燃烧室流围绕着被冷却的壁部件的内壁流动,那也将是有利的。
在附图中示出本发明的实施例。在附图中,
图1是本发明的被冷却壁部件的透视图;
图2是沿图1的II-II平面截取的部份纵向截面图;
图3是沿图1的III-III平面截取的部份纵向截面图;
图4是另一实施例的部份横向截面图;
图5a是包括燃烧室壁的燃烧室的在对流冷却的平面内的部份纵向截面图;
图5b是包括燃烧室壁的燃烧室的在喷射冷却的平面内的部份纵向截面图。
图中只示出对理解本发明是重要的要素。介质的流向以箭头表示。
本发明将在下面借助于实施例和图1至图5进行详细描述。
图1以透视图示出一个被冷却壁部件,在靠近内壁1处设有多个平行于内壁1伸展的纵向冷却通道2。这些纵向冷却通道2通过中间肋3相互连接。在每个冷却通道2的下游端设有一个转向装置4、例如一块弯曲的板,通过这个转向装置纵向冷却通道2分别跟回流冷却通道6相连。这些回流冷却通道6靠近被冷却壁部件的外壁5来设置并在其下侧由中间肋3限定。在每个回流冷却通道6中,在中间肋3的中间部位设有多个成直角朝向内壁1的细管7,这些细管提供一种回流通道6跟内壁1的横向连接。
图2与图3示出图1的部份纵向截面。图2是沿中间壁3与细管7的平面的部份纵向截面,而图3是沿纵向冷却通道2的平面的部份纵向截面。
借助于这些附图就可以看清楚冷却的方式。根据图3,冷却介质11、例如空气或蒸汽、首先流入纵向冷却通道2并在那里对壁部件的内壁1进行对流式冷却。在冷却通道2的下游端冷却介质流11通过转向装置4转向180℃,并按逆流原理流入回流冷却通道6。根据图2,从回流冷却通道6分支出多个成直角朝向被冷却壁部件的内壁1的细管7,这些细管伸展穿过在纵向冷却通道2的中间壁3。冷却介质11现在就从回流通道6穿过这些相互紧密排列的细管7流出并对中间壁3进行对流式冷却。在这里可以称之为喷射冷却,这是因为气态的介质穿过多个小的开孔。在被冷却壁部件的内壁1上,冷却介质形成了一层薄的绝热层,这层绝热层降低了壁的热负荷。
由于用各种不同的冷却技术(对流式冷却、喷射式冷却、薄膜式冷却)的结合来冷却一个经受热负荷的壁部件,通过冷却介质的多次的内部运用,显著地提高了冷却效率。
当然,本发明并不受限于上述的实施例。例如,图4示出一个被冷却壁部件的部份横截面,其中没有多个回流冷却通道,而是只有一个以环形槽道形式呈现的回流冷却通道6。
图5示出一个燃气轮机的燃烧室的部份纵向截面,其中图5a示出沿一个纵向冷却通道的平面的截面,而图5b示出沿中间壁3与细管7的平面的截面。
在图5a中,按本发明的被冷却的壁部件的这个实施例示出成燃烧室冷却衬瓦8。这燃烧室壁1首先按逆流原理被对流冷却,在其中冷却空气11沿着纵向冷却通道2以跟燃烧室流9相反的流向流动。当然也可以按顺流原理来提供对流冷却。在冷却通道2的端头设置有转向装置4来使冷却空气经受一次方向改变。冷却空气转向180℃流入回流通道6。
在图5b中,冷却空气11现在进入在中间壁3中伸展的细管7中。这些细管7分布在冷却通道2的整个长度上,因而使中间壁3以低空气消耗进行冷却。在这个实施例中细管7并不与内壁1成直角设置,而是与在回流通道6内的冷却空气的流向成一锐角,使冷却空气11以一个斜向于燃烧室流9的流向流入燃烧室的内腔。这样,形成在内壁1上的薄膜冷却一绝热层比在例如冷却空气以直角角度进入燃烧室内腔的情况经受更强的附着作用。细管的斜置取向取决于冷却空气的薄膜形成的由流动条件决定的分离现象的强度。
燃烧室内壁因而以低空气消耗实现卓越的冷却,绝热层显著地降低了壁的热负荷。此外,用于冷却目的的混合良好的空气被强有力地引入燃烧室流9内。此外,在预混合燃烧中,绝热层还具有这样的优点,预混合火焰10不会沿壁上的流体边界层向上游移动至燃油喷入处,在那里它将以扩散方式燃烧。
Claims (4)
1.一种被冷却的壁部件,它带有多个靠近内壁(1)并与其平行地伸展的分隔开的对流冷却的纵向冷却通道(2),其中相邻的纵向冷却通道(2)分别通过中间肋(3)相连,其特征在于,在纵向冷却通道(2)的下游端设有转向装置(4),该转向装置与至少一个靠近壁部件的外壁(5)设置的回流冷却通道(6)相连,从该回流冷却通道分支出多个朝向被冷却的壁部件的内壁(1)伸展并设置在中间肋(3)中的细管(7)。
2.按权利要求1所述的被冷却的壁部件,其特征在于,细管(7)与回流冷却通道(6)内的流向成直角设置。
3.按权利要求1所述的被冷却的壁部件,其特征在于,细管(7)与回流冷却通道(6)内的流向成锐角设置。
4.按权利要求1所述的被冷却的壁部件,其特征在于,壁部件是一个燃烧室衬瓦(8)并且燃烧室流(9)围绕着被冷却的壁部件的内壁(1)流动。
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
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DE4443864A DE4443864A1 (de) | 1994-12-09 | 1994-12-09 | Gek}hltes Wandteil |
DEP4443864.8 | 1994-12-09 |
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CN1134505A true CN1134505A (zh) | 1996-10-30 |
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CN95119048A Pending CN1134505A (zh) | 1994-12-09 | 1995-12-06 | 被冷却的壁部件 |
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US (1) | US5647202A (zh) |
EP (1) | EP0716268A3 (zh) |
JP (1) | JPH08233253A (zh) |
CN (1) | CN1134505A (zh) |
DE (1) | DE4443864A1 (zh) |
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CH633347A5 (de) * | 1978-08-03 | 1982-11-30 | Bbc Brown Boveri & Cie | Gasturbine. |
GB2100807B (en) * | 1981-06-30 | 1984-08-01 | Rolls Royce | Turbine blade for gas turbine engines |
US4474014A (en) * | 1981-09-17 | 1984-10-02 | United Technologies Corporation | Partially unshrouded swirler for combustion chambers |
GB2118710B (en) * | 1981-12-31 | 1985-05-22 | Secr Defence | Improvements in or relating to combustion chamber wall cooling |
US4643250A (en) * | 1985-07-01 | 1987-02-17 | Sundstrand Corporation | Fluid jet impingement heat exchanger for operation in zero gravity conditions |
DE3803086C2 (de) * | 1987-02-06 | 1997-06-26 | Gen Electric | Brennkammer für ein Gasturbinentriebwerk |
US4840226A (en) * | 1987-08-10 | 1989-06-20 | The United States Of America As Represented By The United States Department Of Energy | Corrosive resistant heat exchanger |
US5435139A (en) * | 1991-03-22 | 1995-07-25 | Rolls-Royce Plc | Removable combustor liner for gas turbine engine combustor |
DE4137638C2 (de) * | 1991-11-15 | 1994-08-11 | Mtu Muenchen Gmbh | Bauteil mit einer vor thermischer Belastung zu schützenden Wand |
EP0576717A1 (de) * | 1992-07-03 | 1994-01-05 | Abb Research Ltd. | Gasturbinen-Brennkammer |
DE4244302C2 (de) * | 1992-12-28 | 2002-08-29 | Alstom | Vorrichtung zur Prallkühlung |
US5363654A (en) * | 1993-05-10 | 1994-11-15 | General Electric Company | Recuperative impingement cooling of jet engine components |
DE4330037A1 (de) * | 1993-09-06 | 1995-03-09 | Abb Management Ag | Druckwellenmaschine mit integrierter Verbrennung und Verfahren zur Kühlung des Rotors dieser Druckwellenmaschine |
-
1994
- 1994-12-09 DE DE4443864A patent/DE4443864A1/de not_active Withdrawn
-
1995
- 1995-09-19 US US08/530,092 patent/US5647202A/en not_active Expired - Fee Related
- 1995-11-17 EP EP95810721A patent/EP0716268A3/de not_active Withdrawn
- 1995-12-06 CN CN95119048A patent/CN1134505A/zh active Pending
- 1995-12-08 JP JP7320429A patent/JPH08233253A/ja active Pending
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103206880A (zh) * | 2012-01-16 | 2013-07-17 | 波音公司 | 多通道冷却室 |
CN103206880B (zh) * | 2012-01-16 | 2017-01-18 | 波音公司 | 多通道冷却室 |
US10161691B2 (en) | 2012-01-16 | 2018-12-25 | The Boeing Company | Multi-channel cooling plenum |
CN103850801A (zh) * | 2012-11-30 | 2014-06-11 | 阿尔斯通技术有限公司 | 包括近壁冷却布置的燃气涡轮部件 |
CN111237087B (zh) * | 2020-01-19 | 2024-03-22 | 西北工业大学 | 一种航天动力用微孔板主被动复合冷却结构及冷却方法 |
Also Published As
Publication number | Publication date |
---|---|
EP0716268A2 (de) | 1996-06-12 |
JPH08233253A (ja) | 1996-09-10 |
DE4443864A1 (de) | 1996-06-13 |
US5647202A (en) | 1997-07-15 |
EP0716268A3 (de) | 1998-12-23 |
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