EP3538744A1 - Strömungsmaschinenrotor und verfahren zum herstellen desselben - Google Patents
Strömungsmaschinenrotor und verfahren zum herstellen desselbenInfo
- Publication number
- EP3538744A1 EP3538744A1 EP17797639.6A EP17797639A EP3538744A1 EP 3538744 A1 EP3538744 A1 EP 3538744A1 EP 17797639 A EP17797639 A EP 17797639A EP 3538744 A1 EP3538744 A1 EP 3538744A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- alternative
- turbomachine rotor
- lauschaufeln
- hub body
- cover body
- 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.)
- Withdrawn
Links
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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3061—Fixing blades to rotors; Blade roots ; Blade spacers by welding, brazing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/006—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine wheels
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- 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
- F05D2230/10—Manufacture by removing material
-
- 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
- F05D2230/237—Brazing
-
- 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
- F05D2230/238—Soldering
-
- 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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/11—Purpose of the control system to prolong engine life
- F05D2270/114—Purpose of the control system to prolong engine life by limiting mechanical stresses
Definitions
- the invention relates to a turbomachine rotor. Furthermore, the invention relates to a method for producing such a turbomachine rotor.
- Turbomachines such as turbines or compressors, have stator-side modules as well as rotor-side modules.
- To the rotor-side assemblies of a turbomachine includes the so-called Strömungsmaschinenrotor having a radially inner hub body, starting from the hub body radially outwardly extending blades and closed design has a radially outwardly adjoining the blades cover body. Between see the radially inner hub body and the radially outer cover body of a closed Strömungsmaschinenrotors extend the blades of the blades.
- Known closed turbomachinery rotors are constructed such that, according to a first alternative, the blades integral integral part of the hub body and the cover body are materially connected or according to a second alternative, the blades integral integral part of the cover body and are cohesively connected to the hub body.
- turbomachine when the blades are an integral part of the hub body, the blades and the hub body form a monolithic assembly. Then, however, when the blades are an integral part of the cover body, the blades and the cover body form a monolithic assembly.
- turbomachinery rotors can not be operated at increasingly higher speeds, since the cohesive connection, in particular soldered, between the blades and after the first alternative, the cover body or after the second alternative, the hub body at increasingly higher speeds can fail. There is therefore a need for a turbomachine rotor which can be operated at higher speeds.
- the present invention has the object to provide a novel Strömungsmaschinenrotor and a method for producing the same.
- the respective cohesive connection can be improved, in particular stresses are reduced in the area thereof, so that ultimately the turbomachine rotor operated at higher speeds and thus the performance of the turbomachine can be increased.
- the rotor blades have a transition radius between 0.5% and 2.5%, more preferably between 1.0% and 2.0%, in a transition region between the respective blade blade and the respective base. , an outer diameter of the turbomachine rotor is. With such a transition radius between the rotor blade and the base, the strength of the respective cohesive connection and thus the maximum speed of a turbomachine rotor can be increased particularly advantageous.
- Hub body are connected to the sockets of the blades by soldering together.
- a turbomachine rotor can be provided which can be operated at particularly high speeds.
- the inventive method for producing the turbomachine rotor is defined in claim 8.
- 1 shows a highly schematic detail of a first turbomachine rotor; and 2 shows a highly schematic detail of a second turbomachine rotor.
- the invention relates to a turbomachine rotor, namely a so-called a closed turbomachine rotor, in particular a closed turbomachine rotor of a turbine or a compressor.
- Closed turbomachinery rotors have a cover body.
- FIG. 1 shows a highly schematic representation of a detail of a first turbomachine rotor 10 according to the invention with a radially inner hub body 1 1, with a radially outer covering body 12, and with moving blades 13 extending between the radially inner hub body 11 and the radially outer covering body 12 each having a blade blade 14.
- the radially inner hub body 1 1 is also referred to as a hub disc and the radially outer cover body 12 as a cover plate.
- the blades 13 are an integral part of the hub body 1 first
- the blades 13 and the hub body 1 1 thus form a monolithic assembly.
- the blades 13 are materially connected to the cover body 12, in particular by soldering.
- the rotor blades 13 in the exemplary embodiment shown in FIG. 1 are adjacent to the cover body 12, that is to say on one of the cover bodies
- the hub body 1 1, the integral blades 13 of the hub body 1 1 and the integral base 15 of the blades 13 are preferably carried out by milling as an integral assembly.
- the hub body 1 1, the blades 13 and the base 15 thus form a monolithic assembly.
- the blades 13 have in the transition region 1 6 between the respective blade blade 14 and the respective base 15 over a defined transition radius which is greater than the radius in the region of the material connection 17 and between 0.5% and 2.5% of an outer diameter of Turbomachine rotor 10 is.
- This outer diameter of the turbomachine rotor 10 is defined by the largest diameter of the cover body 12.
- the transition radius in the transition region 16 between 0.5% and 2% or between 1, 0% and 2.5%, more preferably between 1, 0% and 2.0%, this outer diameter of the turbomachine rotor 10th
- FIG. 2 shows an alternative embodiment of a turbomachine rotor 20 having a radially inner hub body 21, a radially outer cover body 22, and rotor blades 23 extending between the radially inner hub body 21 and the radially outer hub body 22.
- the blades 23 are an integral part of the cover body 22 and materially connected to the hub body 21, via base 25, which constitute an integral part of the respective blade 23.
- the blades 23, namely the blades 24 of the same, have adjacent to the hub body 21 and at an opposite end of the hub body 21 to the respective base 25 through which the blades 23 are connected to the hub body 21 cohesively.
- FIG. 2 shows a radius in the area of the integral connection 27.
- a defined transition radius is formed, which is greater than the radius in the region of the cohesive connection 27 and between 0.5% and 2.5%, preferably between 0.5% and 2.0% or between 1, 5% and 2.5%, more preferably between 1, 0% and 2.0%, of the outer diameter of the turbomachine rotor 20 is.
- the present invention further relates to a method for producing such a turbomachine rotor 10 or 20.
- a separate cover body 12 or according to the second alternative, a separate hub body 21 is provided.
- These assemblies are preferably each executed by milling or additive manufacturing assemblies.
- hub body 1 1, rotor blades 13 and base 15 form an integral, monolithic assembly made by milling.
- cover body 22, the blades 23 and the base 25 form an integral, monolithic assembly made by milling.
- hub body 1 1 or 21 and cover body 12 or 22 are connected to one another via the base 15 or 25 of the rotor blades 13 and 23, preferably by soldering.
- a transition radius which is preferably formed by milling in the respective transitional region 16, 26 is greater than a radius in the region of the respective integral connection 17, 27. In the variant of FIG. 1, therefore, the transition radius in the transitional region 16 between the base 15 and the intercommunicating blade 14 is greater In the variant of FIG. 2, the transition radius in the transitional region 26 between the base 25 and the intercommunicating blade 24 is greater than the radius in the connection region between the base 25 and the hub body 21.
- the stresses can be reduced by the shaping. Furthermore, speeds at the turbomachine rotor 10, 20 can be increased, whereby ultimately the performance of a turbomachine can be increased.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Non-Positive Displacement Air Blowers (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102016222312.7A DE102016222312A1 (de) | 2016-11-14 | 2016-11-14 | Strömungsmaschinenrotor und Verfahren zum Herstellen desselben |
PCT/EP2017/079077 WO2018087370A1 (de) | 2016-11-14 | 2017-11-13 | Strömungsmaschinenrotor und verfahren zum herstellen desselben |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3538744A1 true EP3538744A1 (de) | 2019-09-18 |
Family
ID=60320892
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP17797639.6A Withdrawn EP3538744A1 (de) | 2016-11-14 | 2017-11-13 | Strömungsmaschinenrotor und verfahren zum herstellen desselben |
Country Status (7)
Country | Link |
---|---|
US (1) | US11078800B2 (de) |
EP (1) | EP3538744A1 (de) |
JP (1) | JP6915052B2 (de) |
KR (1) | KR102270498B1 (de) |
CN (1) | CN109923283B (de) |
DE (1) | DE102016222312A1 (de) |
WO (1) | WO2018087370A1 (de) |
Families Citing this family (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102016222312A1 (de) * | 2016-11-14 | 2018-05-17 | Man Diesel & Turbo Se | Strömungsmaschinenrotor und Verfahren zum Herstellen desselben |
US10774658B2 (en) * | 2017-07-28 | 2020-09-15 | General Electric Company | Interior cooling configurations in turbine blades and methods of manufacture relating thereto |
CN110893533B (zh) * | 2019-12-07 | 2020-11-06 | 湖州师范学院 | 一种空气悬浮轴承高速变频电机叶轮生产工艺 |
Family Cites Families (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2888239A (en) * | 1954-03-15 | 1959-05-26 | Chrysler Corp | Turbine wheel construction |
US3590454A (en) * | 1969-03-03 | 1971-07-06 | Us Air Force | Turbine assembly fabrication |
JPH04123881A (ja) * | 1990-09-11 | 1992-04-23 | Hitachi Ltd | 羽根車およびその電子ビーム溶接方法 |
JP2007125590A (ja) * | 2005-11-04 | 2007-05-24 | Denso Corp | 熱交換器および熱交換器の製造方法 |
EP1785590A1 (de) * | 2005-11-10 | 2007-05-16 | Sulzer Markets and Technology AG | Werkstück sowie Schweissverfahren zur Herstellung eines Werkstücks |
US7637010B2 (en) * | 2005-12-01 | 2009-12-29 | General Electric Company | Methods for machining turbine engine components |
JP4458109B2 (ja) * | 2007-03-27 | 2010-04-28 | 株式会社日立プラントテクノロジー | 溶接溝封止構造 |
EP2183467B2 (de) * | 2007-08-08 | 2023-10-18 | Ansaldo Energia IP UK Limited | Rotoranordnung von einer turbine |
DE102009052882A1 (de) * | 2009-11-13 | 2011-05-19 | Mtu Aero Engines Gmbh | Verfahren und Vorrichtung zur Herstellung eines integral beschaufelten Rotors sowie mittels des Verfahrens hergestellter Rotor |
KR101241669B1 (ko) * | 2009-12-24 | 2013-03-08 | 한국항공우주연구원 | 쉬라우드 타입의 원심 임펠러 및 그 제작방법, 제작 공구 |
JP2011157867A (ja) * | 2010-02-01 | 2011-08-18 | Panasonic Corp | 電動送風機及びそれを用いた電気掃除機 |
US8727729B2 (en) * | 2010-06-29 | 2014-05-20 | Turbocam, Inc. | Method for producing a shrouded impeller from two or more components |
WO2012114404A1 (ja) * | 2011-02-22 | 2012-08-30 | 三菱重工業株式会社 | インペラの製造方法 |
FR2984428B1 (fr) * | 2011-12-19 | 2018-12-07 | Safran Aircraft Engines | Redresseur de compresseur pour turbomachine. |
KR101871942B1 (ko) * | 2012-02-15 | 2018-07-02 | 한화에어로스페이스 주식회사 | 회전 기계의 회전체 및 회전 기계의 회전체 제조 방법 |
US10337401B2 (en) * | 2015-02-13 | 2019-07-02 | United Technologies Corporation | Turbine engine with a turbo-compressor |
US20160237822A1 (en) * | 2015-02-16 | 2016-08-18 | United Technologies Corporation | Blade restoration using shroud plating |
DE102016222312A1 (de) * | 2016-11-14 | 2018-05-17 | Man Diesel & Turbo Se | Strömungsmaschinenrotor und Verfahren zum Herstellen desselben |
US10605101B2 (en) * | 2017-09-12 | 2020-03-31 | United Technologies Corporation | Process of making integrally bladed rotor |
US10792771B2 (en) * | 2017-09-12 | 2020-10-06 | Raytheon Technologies Corporation | Method of making integrally bladed rotor |
-
2016
- 2016-11-14 DE DE102016222312.7A patent/DE102016222312A1/de active Pending
-
2017
- 2017-11-13 EP EP17797639.6A patent/EP3538744A1/de not_active Withdrawn
- 2017-11-13 JP JP2019514799A patent/JP6915052B2/ja active Active
- 2017-11-13 KR KR1020197016594A patent/KR102270498B1/ko active IP Right Grant
- 2017-11-13 CN CN201780070393.5A patent/CN109923283B/zh active Active
- 2017-11-13 US US16/349,551 patent/US11078800B2/en active Active
- 2017-11-13 WO PCT/EP2017/079077 patent/WO2018087370A1/de active Application Filing
Also Published As
Publication number | Publication date |
---|---|
KR20190073574A (ko) | 2019-06-26 |
JP2019534969A (ja) | 2019-12-05 |
US20190264570A1 (en) | 2019-08-29 |
CN109923283B (zh) | 2022-03-18 |
US11078800B2 (en) | 2021-08-03 |
CN109923283A (zh) | 2019-06-21 |
DE102016222312A1 (de) | 2018-05-17 |
KR102270498B1 (ko) | 2021-06-30 |
JP6915052B2 (ja) | 2021-08-04 |
WO2018087370A1 (de) | 2018-05-17 |
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