CN102155298B - 用于噪声减少的喷射器/混合器喷嘴 - Google Patents

用于噪声减少的喷射器/混合器喷嘴 Download PDF

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CN102155298B
CN102155298B CN201110005640.8A CN201110005640A CN102155298B CN 102155298 B CN102155298 B CN 102155298B CN 201110005640 A CN201110005640 A CN 201110005640A CN 102155298 B CN102155298 B CN 102155298B
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张华�
D·W·鲍尔
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General Electric Co
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
    • 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
    • F01D25/30—Exhaust heads, chambers, or the like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
    • F01N1/00—Silencing apparatus characterised by method of silencing
    • F01N1/14—Silencing apparatus characterised by method of silencing by adding air to exhaust gases
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
    • 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
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
    • F02K1/34—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for attenuating noise
    • 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
    • F02K1/36—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto having an ejector
    • 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
    • F02K1/38—Introducing air inside the jet
    • F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
    • 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
    • F02K1/44—Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction
    • 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
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Jet Pumps And Other Pumps (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Abstract

本发明涉及用于噪声减少的喷射器/混合器喷嘴，具体而言，提供了一种燃气涡轮机中的入口放气加热系统，其包括抽取压缩机排气的压缩机排气抽取歧管(12)、接收压缩机排气的入口放气加热歧管(18)、以及设置在入口放气加热歧管的输出端处的多个声频弥散喷嘴(26)，其降低了入口放气加热歧管中的压缩机排气的速度。噪声是由于在周围大气和来自孔的喷气之间的剪切作用而产生的。当利用例如多级喷射器/混合器减慢空气喷射速度时可减少噪声。

Description

用于噪声减少的喷射器/混合器喷嘴
技术领域
本发明涉及燃气涡轮机中的噪声减少，更特别地，涉及在燃气涡轮机入口排热应用中使用多级喷射器/混合器喷嘴来减少噪声。
背景技术
燃气涡轮机的燃烧系统产生热的气体以驱动涡轮。涡轮又驱动压缩机，压缩机提供用于在燃烧系统中进行燃烧的压缩空气。涡轮产生可用的输出功率。
在一些燃气涡轮机应用中，存在燃气涡轮机设备运转的一些情况，在这些情况下燃气涡轮机压力比达到压缩机的运行压力比极限，从而导致压缩机喘振。这些情况可能出现在使用低BTU燃料或任何其它注入大量稀释剂的燃料和/或在寒冷的环境温度条件下的应用中。压缩机压力比典型地大于涡轮压力比，因为后者受到涡轮机燃烧器中的压力损失的影响。
一种用于提供压缩机压力比保护的通常方法是放出燃气涡轮机压缩机排气，并使放气再循环回到压缩机入口。称为入口放气加热(IBH)控制的此燃气涡轮机运行的方法通过将较冷的周围空气与热的压缩机排气的放出部分相混合而提高压缩机进气的入口温度，从而降低流向燃气涡轮机的空气密度和质量流量。
当燃气涡轮机将压缩机空气放出到入口管道中时，其产生了可能超过噪声限度的噪声。现有的设计将放气歧管放置在入口消声板的下游。此布置可解决压缩机IGV的结冰问题，但不会有效解决入口过滤器外壳结冰的问题。如果放气歧管放置在入口管道中的消声器之前来解决结冰问题，则会产生噪声问题。
对于IBH系统提出了一种消声喷嘴。然而消声喷嘴是昂贵的。在航空发动机技术中已经利用喷射器/混合器喷嘴来减少航空发动机噪声而解决了相关问题。噪声由周围大气和来自孔的喷气之间的剪切作用而产生。在多级喷射器/混合器之后，喷射速度显著地减慢，从而减少了噪声。目前在燃气涡轮机中还没有相似的技术来减少噪声。
因而将需要一种IBH系统，其包括喷射器/混合器噪声减少喷嘴，以便在不使用昂贵构件的条件下增强涡轮机中的热空气的混合。
发明内容
在一个示例性实施例中，燃气涡轮机中的入口放气加热系统包括抽取压缩机排气的压缩机排气抽取歧管、接收压缩机排气的入口放气加热歧管、设置在入口放气加热歧管上游的入口过滤器外壳、以及设置在入口放气加热歧管下游的入口消声器。在入口放气加热歧管的输出端以及在入口过滤器外壳和入口消声器之间设置了多个声频弥散喷嘴(acousticdispersionnozzle)。声频弥散喷嘴通过将压缩机排气与入口过滤器外壳之外的空气相混合而用于降低入口放气加热歧管中的压缩机排气的速度。
在另一示例性实施例中，燃气涡轮机中的入口放气加热系统包括抽取压缩机排气的压缩机排气抽取歧管、接收压缩机排气的入口放气加热歧管、以及设置在入口放气加热歧管的输出端处的多个声频弥散喷嘴，其降低入口放气加热歧管中的压缩机排气的速度。
在又另一示例性实施例中，一种用于在燃气涡轮机的入口放气加热系统中减少噪声的方法包括如下步骤：抽取压缩机排气；将压缩机排气引导至入口放气加热歧管中；以及通过将压缩机排气与通过入口过滤器外壳的外部空气相混合而降低入口放气加热歧管中的压缩机排气的速度。
附图说明
图1是包括入口放气加热系统的燃气涡轮机的示意图；
图2是显示了在入口过滤器和入口消声器之间的喷射器/混合器喷嘴的位置的透视图；
图3是图2中所示的入口放气加热歧管的特写图；且
图4是包括示例性喷嘴的入口放气加热歧管的一个分支的详图。
部件列表：
10入口放气加热系统
12压缩机排气抽取歧管
14手动隔离阀
16控制阀
18入口放气加热歧管
20进气过滤器外壳
22入口消声器
24排泄阀
26声频弥散喷嘴
28主歧管
30分支歧管
具体实施方式
参看图1，示意性地图示了入口放气加热系统10。入口放气加热(IBH)典型地用于保护燃气涡轮机压缩机在以降低的IGV角度运行时免于结冰。此外，IBH系统用于在需要额外的压缩机运行安全裕量的某些运行条件下降低压缩机压力比。如图所示，提供了压缩机排气抽取歧管12用于抽取压缩机排气，其通过手动隔离阀14和控制阀16而流向入口放气加热歧管18，该入口放气加热歧管18设置在进气过滤器外壳20和入口消声器22的下游。在所示的系统中，提供了排泄阀24用于使冷凝物转向。
入口放气加热歧管18的输出端包括多个声频弥散喷嘴26。喷嘴26通过将压缩机排气与入口过滤器外壳20之外的空气相混合而用于降低入口放气加热歧管18中的压缩机排气的速度。图2显示了入口放气加热歧管18的输出端，该入口放气加热歧管18定位在入口过滤器外壳20和入口消声器22之间。参看图2和图3，入口放气加热歧管18包括主歧管28和连接在主歧管28上的多个分支歧管30。声频弥散喷嘴26设置在分支岐管30上。图4是分支岐管30和示例性喷嘴26的特写图。本领域中的普通技术人员将会领会用于喷嘴26的备选的合适设计，并且本发明并不意味着局限于图4中图示的示例性喷嘴。
所述系统结合了一种喷射器/混合器噪声减少喷嘴，从而在不使用昂贵构件的条件下增强涡轮中的热空气的混合。通过在喷射器/混合器喷嘴中使压缩机排气与入口过滤器外壳之外的空气相混合可降低入口放气加热歧管中的压缩机排气的速度，从而减少噪声。
虽然已经结合目前被认为是最可行且最优选的实施例描述了本发明，但是应该懂得本发明并不局限于所公开的实施例，相反，其意图覆盖包含在所附权利要求的精神和范围内的各种变体和等效装置。

Claims (8)

1.一种燃气涡轮机中的入口放气加热系统，包括：
压缩机排气抽取歧管(12)，其抽取压缩机排气；
接收压缩机排气的入口放气加热歧管(18)；
设置在所述入口放气加热歧管上游的入口过滤器外壳(20)；
设置在所述入口放气加热歧管下游的入口消声器(22)；和
多个声频弥散喷嘴(26)，其设置在所述入口放气加热歧管的输出端处以及所述入口过滤器外壳和所述入口消声器之间，所述声频弥散喷嘴通过将压缩机排气与来自所述入口过滤器外壳的外部空气混合而降低所述入口放气加热歧管中的压缩机排气的速度。
2.根据权利要求1所述的入口放气加热系统，其特征在于，所述多个声频弥散喷嘴(26)包括喷射器/混合器噪声减少喷嘴。
3.根据权利要求1所述的入口放气加热系统，其特征在于，所述入口放气加热歧管(18)包括主歧管(28)和连接在所述主歧管上的多个分支歧管(30)，并且其中所述多个声频弥散喷嘴(26)设置在所述分支歧管上。
4.一种燃气涡轮机中的入口放气加热系统，包括：
压缩机排气抽取歧管(12)，其抽取压缩机排气；
接收压缩机排气的入口放气加热歧管(18)；和
多个声频弥散喷嘴(26)，其设置在所述入口放气加热歧管的输出端处，所述多个声频弥散喷嘴通过将压缩机排气与来自入口过滤器外壳的外部空气混合而降低了所述入口放气加热歧管中的压缩机排气的速度，所述多个声频弥散喷嘴设置于所述入口过滤器外壳和入口消声器之间。
5.根据权利要求4所述的入口放气加热系统，其特征在于，所述多个声频弥散喷嘴(26)包括喷射器/混合器噪声减少喷嘴。
6.根据权利要求4所述的入口放气加热系统，其特征在于，所述入口放气加热歧管(18)包括主歧管(28)和连接在所述主歧管上的多个分支歧管(30)，并且其中所述多个声频弥散喷嘴(26)设置在所述分支歧管上。
7.一种用于在燃气涡轮机的入口放气加热系统中减少噪声的方法，所述方法包括：
抽取压缩机排气；
将压缩机排气引导至入口放气加热歧管(18)中；并
通过将压缩机排气与经由入口过滤器外壳(20)的外部空气混合来降低所述入口放气加热歧管中的压缩机排气的速度；
其中，所述降低步骤包括通过设置在所述入口放气加热歧管的输出端处以及所述入口过滤器外壳(20)和入口消声器(22)之间的多个声频弥散喷嘴(26)而使所述入口放气加热歧管(18)排气。
8.根据权利要求7所述的方法，其特征在于，所述入口放气加热歧管(18)包括主歧管(28)和连接在所述主歧管上的多个分支歧管(30)，并且其中所述方法包括将所述声频弥散喷嘴(26)设置在所述分支歧管上。
CN201110005640.8A 2010-01-04 2011-01-04 用于噪声减少的喷射器/混合器喷嘴 Expired - Fee Related CN102155298B (zh)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP5010499B2 (ja) * 2008-02-28 2012-08-29 三菱重工業株式会社 ガスタービン及びガスタービンの保守点検方法
US8932004B2 (en) * 2011-11-08 2015-01-13 General Electric Company Inlet bleed heat system
US8926265B2 (en) * 2011-11-08 2015-01-06 General Electric Company Inlet bleed heat system
US8844258B2 (en) * 2011-11-23 2014-09-30 General Electric Company Systems and methods for de-icing a gas turbine engine inlet screen and dehumidifying inlet air filters
MX358183B (es) * 2012-04-02 2018-08-08 Powerphase Llc Sistema, metodo y aparato para inyeccion de aire comprimido para motores de turbina de combustion interna.
JP5984535B2 (ja) * 2012-07-03 2016-09-06 三菱日立パワーシステムズ株式会社 ガスタービンの氷結防止方法
CN104769256B (zh) 2012-10-26 2019-01-18 鲍尔法斯有限责任公司 燃气轮机能量补充系统和加热系统
US9157333B2 (en) * 2012-11-06 2015-10-13 General Electric Company Inlet bleed heat system with integrated air knife/silencer panels
FR2997996B1 (fr) * 2012-11-12 2015-01-09 Snecma Support de tube d'evacuation d'air dans une turbomachine
US9447732B2 (en) * 2012-11-26 2016-09-20 General Electric Company Gas turbine anti-icing system
US9470150B2 (en) 2013-04-30 2016-10-18 General Electric Company Gas turbine power augmentation system
EP2824285B1 (en) * 2013-07-11 2016-03-16 Alstom Technology Ltd Gas turbine engine comprising an inlet flow control arrangement
EP2837794A1 (en) * 2013-08-14 2015-02-18 Alstom Technology Ltd Improved intake arrangement in gas turbine power plant
US9359951B2 (en) * 2013-09-06 2016-06-07 General Electric Company Inlet bleed heat system and related method for a compact gas turbine inlet
US9494050B2 (en) 2013-09-20 2016-11-15 The Boeing Company Concentric nozzles for enhanced mixing of fluids
US10036321B2 (en) * 2014-05-29 2018-07-31 General Electric Company Systems and methods for utilizing gas turbine compartment ventilation discharge air
US9771865B2 (en) 2014-10-28 2017-09-26 General Electric Company Inlet bleed heat manifold including acoustically treated feed pipe
US10066632B2 (en) * 2015-12-10 2018-09-04 General Electric Company Inlet bleed heat control system
US10704464B2 (en) 2016-02-16 2020-07-07 General Electric Company Acoustic nozzles for inlet bleed heat systems
US20170292456A1 (en) * 2016-04-12 2017-10-12 General Electric Company Integrated gas turbine inlet silencer and bleed heat system
US10215193B2 (en) 2017-01-31 2019-02-26 Meggitt Aerospace Ltd. Valve assembly
US20180274445A1 (en) * 2017-03-21 2018-09-27 General Electric Company Inlet Bleed Heat Duct Assembly
US10968828B2 (en) * 2019-03-06 2021-04-06 General Electric Company Anti-icing system for a gas turbine
CN110454285A (zh) * 2019-09-06 2019-11-15 烟台杰瑞石油装备技术有限公司 一种涡轮发动机的隔声舱体
US11391207B2 (en) 2020-01-16 2022-07-19 General Electric Company Anti-icing system having a nozzle with a deflector plate and method
US11473501B2 (en) * 2020-12-22 2022-10-18 General Electric Company Anti-icing for gas turbine system
US11459951B2 (en) * 2020-12-22 2022-10-04 General Electric Company Anti-icing system with a flow-deflector assembly

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5157916A (en) * 1990-11-02 1992-10-27 United Technologies Corporation Apparatus and method for suppressing sound in a gas turbine engine powerplant
CN1086581A (zh) * 1992-11-03 1994-05-11 程大酉 改进的回热并联复合双流体热机
US5560195A (en) * 1995-02-13 1996-10-01 General Electric Co. Gas turbine inlet heating system using jet blower
US5761900A (en) * 1995-10-11 1998-06-09 Stage Iii Technologies, L.C. Two-stage mixer ejector suppressor
US6082635A (en) * 1996-06-12 2000-07-04 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Undulated nozzle for enhanced exit area mixing
US6250064B1 (en) * 1999-05-07 2001-06-26 General Electric Co. Gas turbine inlet air integrated water saturation and supersaturation system and related process
CN1582364A (zh) * 2001-11-02 2005-02-16 阿尔斯通技术有限公司 燃气涡轮机组

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2877098B2 (ja) * 1995-12-28 1999-03-31 株式会社日立製作所 ガスタービン，コンバインドサイクルプラント及び圧縮機
US6027304A (en) * 1998-05-27 2000-02-22 General Electric Co. High pressure inlet bleed heat system for the compressor of a turbine
US6226974B1 (en) * 1999-06-25 2001-05-08 General Electric Co. Method of operation of industrial gas turbine for optimal performance
JP3713173B2 (ja) * 1999-12-15 2005-11-02 株式会社日立製作所 ガスタービンの氷結防止運転方法
US8136361B2 (en) * 2006-05-04 2012-03-20 General Electric Company Methods and apparatus for assembling a low noise ejector motive nozzle
US7698898B2 (en) * 2007-04-04 2010-04-20 General Electric Company Mixer for cooling and sealing air system for turbomachinery
US8001789B2 (en) * 2008-03-26 2011-08-23 Alstom Technologies Ltd., Llc Utilizing inlet bleed heat to improve mixing and engine turndown

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5157916A (en) * 1990-11-02 1992-10-27 United Technologies Corporation Apparatus and method for suppressing sound in a gas turbine engine powerplant
CN1086581A (zh) * 1992-11-03 1994-05-11 程大酉 改进的回热并联复合双流体热机
US5560195A (en) * 1995-02-13 1996-10-01 General Electric Co. Gas turbine inlet heating system using jet blower
US5761900A (en) * 1995-10-11 1998-06-09 Stage Iii Technologies, L.C. Two-stage mixer ejector suppressor
US6082635A (en) * 1996-06-12 2000-07-04 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Undulated nozzle for enhanced exit area mixing
US6250064B1 (en) * 1999-05-07 2001-06-26 General Electric Co. Gas turbine inlet air integrated water saturation and supersaturation system and related process
CN1582364A (zh) * 2001-11-02 2005-02-16 阿尔斯通技术有限公司 燃气涡轮机组

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