CN109312626B - 用于涡轮隔板的静止叶片及相关联的涡轮隔板 - Google Patents
用于涡轮隔板的静止叶片及相关联的涡轮隔板 Download PDFInfo
- Publication number
- CN109312626B CN109312626B CN201780038742.5A CN201780038742A CN109312626B CN 109312626 B CN109312626 B CN 109312626B CN 201780038742 A CN201780038742 A CN 201780038742A CN 109312626 B CN109312626 B CN 109312626B
- Authority
- CN
- China
- Prior art keywords
- stationary blade
- airfoil
- trailing edge
- leading edge
- reinforcement
- 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.)
- Active
Links
- 230000002787 reinforcement Effects 0.000 claims abstract description 16
- 125000006850 spacer group Chemical group 0.000 claims description 26
- 238000010276 construction Methods 0.000 claims description 13
- 230000003014 reinforcing effect Effects 0.000 claims description 5
- 229910000851 Alloy steel Inorganic materials 0.000 claims description 3
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 3
- 229910052804 chromium Inorganic materials 0.000 claims description 3
- 239000011651 chromium Substances 0.000 claims description 3
- 239000000956 alloy Substances 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
- 229910000831 Steel Inorganic materials 0.000 claims 1
- 239000010959 steel Substances 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 description 4
- 238000005192 partition Methods 0.000 description 3
- 239000011324 bead Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 239000002131 composite material Substances 0.000 description 1
- 238000005242 forging Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Images
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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- 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
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
-
- 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
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
- F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
-
- 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
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/31—Application in turbines in steam turbines
-
- 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
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
-
- 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
- F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
-
- 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
- F05D2240/128—Nozzles
-
- 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
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/304—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the trailing edge of a rotor blade
-
- 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
- F05D2240/80—Platforms for stationary or moving blades
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
用于轴流式涡轮的静止叶片(32),包括翼型件部分(44),其具有前缘(44a)、后缘(44b)、压力侧和吸入侧,以及包括与所述翼型件部分(44)整体结合的径向内增强部分(46)和外增强部分(48)。每个增强部分(46,48)紧密地遵循翼型件部分(44)的区段的形状。
Description
技术领域
本发明涉及用于轴流式涡轮(axial flow turbine)的静止叶片的环构造,且具体地涉及蒸汽涡轮。
具体而言,本发明涉及涡轮隔板(turbine diaphragm)。
背景技术
蒸汽涡轮是旨在用于将蒸汽的热转换成用于驱动交流发电机、泵或任何其它旋转机械接收器的机械能的旋转机器(rotating machine)。大体上,蒸汽涡轮包括高压模块、中压模块和低压模块。
蒸汽涡轮大体上包括对称或非对称的单或双流动内体,其包围配备有移动叶片的转子,且支承固定或静止叶片,形成了悬置在所述内体中的隔板。隔板适于沿朝转子的移动叶片的特定方向引导蒸汽流,从而加速蒸汽流。
本发明涉及已知构造类型的隔板,称为“间隔带隔板”和“平台隔板”。
在图1a中所示的所谓的“间隔带隔板”构造类型10中,叶片翼型件11借助于从平条折叠的内环形带14和外环形带15沿径向固定至内环12和外环13。例如,借助于激光在所述带14,15中切割通孔16,以匹配翼型件形状的横截面。翼型件11的端部然后插入所述通孔16,且角焊就位。内带14继而又焊接至内环12,且外带15继而又焊接至外环13。相比于蒸汽涡轮中使用的其它构造类型,此构造类型涉及叶片的相对少量的机加工。
例如,在图1b中所示的所谓“平台隔板”构造类型20中,叶片翼型件21具有基本上以导叶的形状的区段,其具有与径向内平台22和径向外平台23整体结合的其两个相对端部。叶片翼型件和平台由实心杆或通过锻造机加工。静止叶片的整个环带通过将连续的组合翼型件平台构件组装在内环与外环(未示出)之间且通过将平台焊接至所述环来构成。由于该平台,此隔板相比于间隔带类型具有更好的机械强度,但具有更高的制造成本。
发明内容
本发明的目的在于弥补以上缺陷。
本发明的一个具体目的在于提供一种类型的隔板构造,其具有良好的性能特征且制造经济。
在一个实施例中,用于轴流式涡轮的静止叶片包括翼型件部分,其具有前缘、后缘、压力侧和吸入侧,以及与所述翼型件部分整体结合的径向内增强部分和外增强部分。
每个增强部分紧密地遵循翼型件部分区段的形状。
由于增强部分,故间隔带隔板的机械强度提高,而不增加制造成本。
有利地,每个增强部分具有基本上大于翼型件部分的区段的区段。增强部分的区段具有对应于包绕翼型件部分的前缘的前缘的圆形且扩大的形状,以及对应于包绕翼型件部分后缘的后缘的较薄部分。
静止叶片壳可由合金钢材料制成,例如,包括12%的铬。
根据第二方面,本发明涉及一种轴流式涡轮隔板构造,其包括如前文所述的多个相同静止叶片的环带、其中具有成形为接收每个静止叶片的内增强部分和外增强部分的通孔的内间隔带和外间隔带、以及包绕环形间隔带的径向内隔板环和外隔板环。
在一个实施例中,每个增强部分通过焊缝(weld)来焊接至对应的间隔带。
例如,焊缝位于每个增强部分的每个前缘和后缘处。
在一个实施例中,内间隔带焊接至内环,且外带焊接至外环。
附图说明
从研究由完全非限制性的示例考虑且由附图示出的许多实施例的详细描述中将更好理解本发明,在附图中:
图1a示出了已知间隔带涡轮隔板构造类型;
图1b示出了用于已知平台涡轮隔板构造类型中的具有整体平台的固定叶片;
图2为根据本发明的一个实施例的蒸汽涡轮隔板的一部分的三维透视图;
图3为用于图2的隔板构造中的静止叶片的三维透视图;
图4为图3的静止叶片的上方视图;以及
图5为焊接到图2的蒸汽涡轮隔板的间隔带上的图3的静止叶片的径向横截面。
具体实施方式
示例性实施例的以下详细描述参照了附图。不同图中的相同参考标号表示相同或类似的元件。此外,图不一定按比例绘制。
如图2上所示,涡轮的蒸汽涡轮隔板30的一部分包括喷嘴单元,其具有借助于从平条折叠的内环形间隔带38和外环形间隔带40沿径向固定至内环34和外环36的多个相同的静止叶片翼型件32。
内环34和外环36、以及内间隔带38和外间隔带40是同心的。
内间隔带38和外间隔带40分别设有通孔38a,40a。如所示,通孔通向两端,以接收静止叶片。例如,通孔38a,40可例如借助于激光在所述间隔带38,40中切割,以匹配翼型件形状的横截面。翼型件32的端部然后插入所述通孔,且角焊就位。内间隔带38继而又焊接至内环34,且外带40继而又焊接至外环36。
如图3和4上所示,每个静止叶片32具有翼型件部分44,其具有细长本体,该细长本体具有与内间隔带38接触的内端32a,以及与外间隔带40接触的与所述内端32a相对的外端32b。
内端32a和外端32b分别通过借助于布置在所述端部与所述间隔带之间的焊珠(weld bead,有时也称为焊道)的焊接来连接至内间隔带38和外间隔带40。以此方式,每个静止叶片焊接至内间隔带和外间隔带两者。
例如,每个静止叶片32具有如图4上所示的基本上以导叶的形状的区段,其具有对应于前缘44a的圆形且扩大的形状和对应于后缘44b的较薄部分。
如图3和4上所示,每个静止叶片32的内端32a和外端32b分别设有内增强部分46和外增强部分48。每个增强部分46,48具有略大于翼型件部分44的区段的区段,如图4上所示,其具有对应于前缘46a,48a的圆形且扩大的形状和对应于后缘46b,48b的较薄部分。
每个增强部分46,48包绕对应端部的整个区段的外周,以便具有基本上大于翼型件部分44的区段的区段。因此,增强部分46,48的形状在其整体上近似翼型件部分44的区段的形状,即,在前缘44a和后缘44b、以及翼型件部分44的吸入侧和压力侧处和附近。
如图5上所示,第一增强部分46和第二增强部分48滑入间隔带38,40的其匹配通孔38a,40a中。一旦所有静止叶片32已经组装到间隔带38,40中,它们必须牢固地焊接就位。每个增强部分的每个前缘和后缘通过焊缝50a,50b和52a,52b焊接至对应的间隔带。焊缝50a,50b和52a,52b在图4上以阴影线(hatched line)示出。
静止叶片32由合金钢材料制成,例如具有12%的铬。
由于设在翼型件部分的每个端部处的增强部分,静止叶片增强。
由于本发明,隔板构造具有良好的机械强度,同时制造经济且容易。
Claims (8)
1.一种用于轴流式涡轮的静止叶片(32),包括:
翼型件部分(44),其具有前缘(44a)、后缘(44b)、压力侧和吸入侧,
与所述翼型件部分(44)整体结合的径向内增强部分(46)和外增强部分(48),
其中每个增强部分(46,48)紧密地遵循所述翼型件部分(44)的区段的形状,且
其中,在所述前缘(44a)处所述内增强部分(46)和外增强部分(48)之间的距离比在所述后缘(44b)处所述内增强部分(46)和外增强部分(48)之间的距离更长。
2.根据权利要求1所述的静止叶片,其中,每个增强部分(46,48)具有实质上大于所述翼型件部分(44)的区段的区段,其具有对应于包绕所述翼型件部分(44)的前缘(44a)的所述增强部分(46,48)的前缘(46a,48a)的圆形且扩大的形状,以及对应于包绕所述翼型件部分(44)的后缘(44b)的所述增强部分(46,48)的后缘(46b,48b)的较薄部分。
3.根据权利要求1或2所述的静止叶片,由合金钢材料制成。
4.根据权利要求3所述的静止叶片,其中,所述合金钢材料包括12%的铬。
5.一种轴流式涡轮隔板构造,包括:
根据前述权利要求中任一项所述的多个相同的静止叶片的环带,
内间隔带(38)和外间隔带(40),所述内间隔带(38)和外间隔带(40)具有其中的通孔(38a,40a),所述通孔(38a,40a)成形为以接收每个静止叶片(32)的内增强部分(46)和外增强部分(48),以及
包绕所述内间隔带(38)和外间隔带(40)的径向内隔板环(34)和外隔板环(36)。
6.根据权利要求5所述的轴流式涡轮隔板构造,其中,每个增强部分通过焊缝(50a,50b;52a,52b)焊接至所述内间隔带(38)和外间隔带(40)的对应其中之一上。
7.根据权利要求6所述的轴流式涡轮隔板构造,其中,所述焊缝(50a,50b;52a,52b)位于每个增强部分(46,48)的每个前缘(48a,46a)和后缘(48b,48b)处。
8.根据权利要求5至7中任一项所述的轴流式涡轮隔板构造,其中,所述内间隔带(38)焊接至所述内隔板环(34),且所述外间隔带(40)焊接至所述外隔板环(36)。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP16290110.2A EP3260663B1 (en) | 2016-06-21 | 2016-06-21 | Axial flow turbine diaphragm construction |
EP16290110.2 | 2016-06-21 | ||
PCT/EP2017/065220 WO2017220646A1 (en) | 2016-06-21 | 2017-06-21 | Static blade for a turbine diaphragm and associated turbine diaphragm |
Publications (2)
Publication Number | Publication Date |
---|---|
CN109312626A CN109312626A (zh) | 2019-02-05 |
CN109312626B true CN109312626B (zh) | 2022-06-24 |
Family
ID=56787385
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201780038742.5A Active CN109312626B (zh) | 2016-06-21 | 2017-06-21 | 用于涡轮隔板的静止叶片及相关联的涡轮隔板 |
Country Status (5)
Country | Link |
---|---|
US (1) | US20200182076A1 (zh) |
EP (1) | EP3260663B1 (zh) |
JP (1) | JP6972035B2 (zh) |
CN (1) | CN109312626B (zh) |
WO (1) | WO2017220646A1 (zh) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US11879360B2 (en) * | 2020-10-30 | 2024-01-23 | General Electric Company | Fabricated CMC nozzle assemblies for gas turbine engines |
CN112377278B (zh) * | 2020-10-30 | 2023-04-28 | 北京国能龙威发电技术有限公司 | 一种汽轮机自带冠拂配式隔板的整圈装配方法 |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2681788A (en) * | 1951-05-23 | 1954-06-22 | Solar Aircraft Co | Gas turbine vane structure |
EP1847689A2 (en) * | 2006-04-21 | 2007-10-24 | General Electric Company | Apparatus and method of diaphragm assembly |
CN101280693A (zh) * | 2008-05-23 | 2008-10-08 | 无锡润和叶片制造有限公司 | 1000mw汽轮机扭曲马刀叶片及制备方法 |
CN102534309A (zh) * | 2010-12-28 | 2012-07-04 | 株式会社日立制作所 | Ni基合金、及使用其的燃气轮机的涡轮动叶和静叶 |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4464094A (en) * | 1979-05-04 | 1984-08-07 | Trw Inc. | Turbine engine component and method of making the same |
US4728258A (en) * | 1985-04-25 | 1988-03-01 | Trw Inc. | Turbine engine component and method of making the same |
US5474419A (en) * | 1992-12-30 | 1995-12-12 | Reluzco; George | Flowpath assembly for a turbine diaphragm and methods of manufacture |
US5765993A (en) * | 1996-09-27 | 1998-06-16 | Chromalloy Gas Turbine Corporation | Replacement vane assembly for fan exit guide |
US6579061B1 (en) * | 2001-07-27 | 2003-06-17 | General Electric Company | Selective step turbine nozzle |
GB2436597A (en) * | 2006-03-27 | 2007-10-03 | Alstom Technology Ltd | Turbine blade and diaphragm |
US7761990B2 (en) * | 2006-09-26 | 2010-07-27 | Pas Technologies, Inc. | Method of repairing a stationary airfoil array directing three-dimensional flow |
CN201071738Y (zh) * | 2007-08-20 | 2008-06-11 | 如皋透平叶片制造有限公司 | 一种工业汽轮机静叶 |
US8684698B2 (en) * | 2011-03-25 | 2014-04-01 | General Electric Company | Compressor airfoil with tip dihedral |
-
2016
- 2016-06-21 EP EP16290110.2A patent/EP3260663B1/en active Active
-
2017
- 2017-06-21 US US16/312,618 patent/US20200182076A1/en not_active Abandoned
- 2017-06-21 CN CN201780038742.5A patent/CN109312626B/zh active Active
- 2017-06-21 WO PCT/EP2017/065220 patent/WO2017220646A1/en active Application Filing
- 2017-06-21 JP JP2018566573A patent/JP6972035B2/ja active Active
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2681788A (en) * | 1951-05-23 | 1954-06-22 | Solar Aircraft Co | Gas turbine vane structure |
EP1847689A2 (en) * | 2006-04-21 | 2007-10-24 | General Electric Company | Apparatus and method of diaphragm assembly |
CN101280693A (zh) * | 2008-05-23 | 2008-10-08 | 无锡润和叶片制造有限公司 | 1000mw汽轮机扭曲马刀叶片及制备方法 |
CN102534309A (zh) * | 2010-12-28 | 2012-07-04 | 株式会社日立制作所 | Ni基合金、及使用其的燃气轮机的涡轮动叶和静叶 |
Also Published As
Publication number | Publication date |
---|---|
US20200182076A1 (en) | 2020-06-11 |
EP3260663A1 (en) | 2017-12-27 |
CN109312626A (zh) | 2019-02-05 |
JP6972035B2 (ja) | 2021-11-24 |
JP2019518903A (ja) | 2019-07-04 |
WO2017220646A1 (en) | 2017-12-28 |
EP3260663B1 (en) | 2020-07-29 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP2620591B1 (en) | Gas turbine engine stator vane assembly with inner shroud | |
EP1852575B1 (en) | Stationary blade ring of axial compressor | |
KR102228248B1 (ko) | 고강도 터보기계 임펠러, 상기 임펠러를 포함하는 터보기계 및 제조 방법 | |
EP2935789B2 (en) | Airfoil assembly with paired endwall contouring | |
US20140286761A1 (en) | Centrifugal compressor | |
US9957980B2 (en) | Vane with sealed lattice in a shroud of an axial turbomachine compressor | |
GB2436597A (en) | Turbine blade and diaphragm | |
CN104011333B (zh) | 涡轮机组压气机导向叶片组件 | |
CN109312626B (zh) | 用于涡轮隔板的静止叶片及相关联的涡轮隔板 | |
US20160215640A1 (en) | Feather seal | |
US3107897A (en) | Gas turbine nozzle and vane assembly | |
EP3123002B1 (en) | Stator vane support system within a gas turbine engine | |
US20070071605A1 (en) | Integrated nozzle and bucket wheels for reaction steam turbine stationary components and related method | |
CN110130999B (zh) | 用于轴流式涡轮发动机的结构壳体 | |
EP1764482A2 (en) | Single piece nozzle wheel and manufacturing method | |
US20200024998A1 (en) | Turbine engine vane arrangement having a plurality of interconnected vane arrangement segments | |
EP1582698A1 (en) | Integral covered nozzle with attached overcover | |
JP2019094900A (ja) | タービンガイド装置 | |
US10267158B2 (en) | Airfoil fillet | |
US9863253B2 (en) | Axial turbomachine compressor blade with branches at the base and at the head of the blade | |
US20240183279A1 (en) | Group of stator vanes |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PB01 | Publication | ||
PB01 | Publication | ||
SE01 | Entry into force of request for substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
GR01 | Patent grant | ||
GR01 | Patent grant |