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1. CN107735548 - TURBINE BLADE

Amt China
Aktenzeichen/Anmeldenummer 201680039384.5
Anmeldedatum 21.06.2016
Veröffentlichungsnummer 107735548
Veröffentlichungsdatum 23.02.2018
Erteilungsnummer 107735548
Erteilungsdatum 12.07.2019
Veröffentlichungsart B
IPC
F01D 5/14
FSektion F Maschinenbau; Beleuchtung; Heizung; Waffen; Sprengen
01Kraft- und Arbeitsmaschinen oder Kraftmaschinen allgemein; Kraftanlagen allgemein; Dampfkraftmaschinen
DStrömungsmaschinen , z.B. Dampfturbinen
5Schaufeln; Schaufelträger; Heizung, Wärmedämmung, Kühlung, Schwingungsverhütung an Schaufeln
12Schaufeln
14Schaufelform
CPC
F01D 5/14
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
5Blades; Blade-carrying members
12Blades
14Form or construction
F01D 5/147
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
5Blades; Blade-carrying members
12Blades
14Form or construction
147Construction, i.e. structural features, e.g. of weight-saving hollow blades
F05D 2230/21
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2230Manufacture
20essentially without removing material
21by casting
F01D 9/041
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
9Stators
02Nozzles; Nozzle boxes; Stator blades; Guide conduits ; , e.g. individual nozzles
04forming ring or sector
041using blades
F05D 2220/32
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2220Application
30in turbines
32in gas turbines
F05D 2240/12
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2240Components
10Stators
12Fluid guiding means, e.g. vanes
Anmelder SIEMENS AG
西门子股份公司
Erfinder BUCHHOLZ BJORN
B·布赫霍尔兹
GOSSILIN RALPH
R·格西林
KOCH DANIELA
D·科赫
SCHULER MARCO
M·舒勒
Vertreter 北京市金杜律师事务所 11256
Prioritätsdaten 15175301 03.07.2015 EP
Titel
(EN) TURBINE BLADE
(ZH) 涡轮机叶片
Zusammenfassung
(EN)
The invention relates to a cast turbine blade (10) having a platform (16) and a hollow blade airfoil (18) arranged thereon, wherein the blade airfoil (18) has a pressure-side blade wall (34) and a suction-side blade wall (32) that extend, along a centrally arranged curved profile centerline (42), from a common leading edge (28) to a common trailing edge (30), and having a transition (36), with anouter contour profile, between the blade airfoil and the platform (36), wherein the blade walls (32, 34) each have a locally determined blade wall thickness (D), wherein the turbine blade has, internally, a contour profile that partially matches the outer contour profile of the transition (36) such that the region of the transition (36) has an essentially constant blade wall thickness. In order tofurther improve the service life of such a turbine blade, it is provided that, in the transition (36), the contour profile at a surface section (40) of the blade airfoil facing the leading edge (28)is such that the blade wall thickness is increased there in comparison to the blade wall thickness of the transition away from the leading edge.

(ZH)
本发明涉及一种具有平台(16)并具有布置在其上的中空叶片翼型(18)的铸造涡轮机叶片(10),其中叶片翼型(18)具有沿居中布置的弯曲外形中心线(42)从公共的前缘(28)延伸到公共的后缘(30)的压力侧叶片壁(34)和吸力侧叶片壁(32),并且涡轮机叶片(10)具有在叶片翼型和平台(36)之间的具有外轮廓外形的过渡部(36),其中叶片壁(32、34)均具有局部地确定的叶片壁厚(D),其中涡轮机叶片在内部具有部分地适应于过渡部(36)的外轮廓外形的轮廓外形,使得过渡部(36)的区域具有基本均匀的叶片壁厚。为了进一步改善这种涡轮机叶片的使用寿命,提供了在过渡部(36)中,叶片翼型的面向前缘(28)的表面部分(40)处的轮廓外形使得:与远离前缘的过渡部的叶片壁厚相比,此处的叶片壁厚增加。