US20020014006A1 - Process and blank for preparing rhomboidal blades for axial turbo engines - Google Patents

Process and blank for preparing rhomboidal blades for axial turbo engines Download PDF

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Publication number
US20020014006A1
US20020014006A1 US09/904,276 US90427601A US2002014006A1 US 20020014006 A1 US20020014006 A1 US 20020014006A1 US 90427601 A US90427601 A US 90427601A US 2002014006 A1 US2002014006 A1 US 2002014006A1
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US
United States
Prior art keywords
blade
rhomboidal
blank
section
cross
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.)
Abandoned
Application number
US09/904,276
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English (en)
Inventor
Hans-Egon Brock
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MAN Turbo AG
Original Assignee
MAN Turbomaschinen AG GHH Borsig
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by MAN Turbomaschinen AG GHH Borsig filed Critical MAN Turbomaschinen AG GHH Borsig
Assigned to MAN TURBOMASCHINEN AG GHH BORSIG reassignment MAN TURBOMASCHINEN AG GHH BORSIG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BROCK, HANS-EGON
Publication of US20020014006A1 publication Critical patent/US20020014006A1/en
Priority to US10/620,033 priority Critical patent/US6910270B2/en
Abandoned legal-status Critical Current

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Classifications

    • 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
    • B23P15/02—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
    • 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
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49995—Shaping one-piece blank by removing material

Definitions

  • the present invention pertains to a process and a blank for preparing rhomboidal blades for an axial turbo, the blades including a blade footing of a rhomboidal cross section and a blade body for axial turbo engines, in which the blade is worked out of a solid blank by machining.
  • the blank for manufacturing the rhomboidal blade includes a blade footing of rhomboidal shape and a blade body for axial turbo engines by machining to the finished size of the blade.
  • Rhomboidal blades are used as rotor blades and guide vanes in axial turbo engines, such as turbines and axial compressors. These rhomboidal blades are characterized by a blade footing, whose cross section has the shape of a rhomboid or parallelogram with sides of equal length or with unequal sides in pairs. The advantage of this cross-sectional shape is that more blades can be accommodated on the circumference of the rotor or stator of the axial turbo engine than in the case of blades with a rectangular blade footing.
  • the manufacturers of the engines have always used a hot-rolled, rectangular flat steel or wide flat steel as the input stock for manufacturing the blades, from which the blade was machined by working from the solid.
  • the rectangular flat or wide flat steel can be manufactured simply and consequently at a reasonable cost according to the rolling technology. If certain minimum amounts are purchased, the manufacturer is ready to deliver dimensions according to the customer's wishes.
  • the length of the blade must always be arranged in the direction of rolling in all bars for reasons of strength.
  • the rectangular flat steel is determined according to the maximum dimensions of the blade plus oversize for machining. Only one blade is arranged in the bar. The rectangular flat steel is then machined all around to obtain the desired rhomboidal cross-sectional shape of the blade. Depending on the size of the rhomboid angle, very much material must be removed by machining until the desired blade blank is obtained.
  • Smaller blades are manufactured by some engine manufacturers from wide flat steels. A plurality of blades are arranged next to one another in the bar. The wide flat steel is cut by oblique sawing into a plurality of rhomboidal parts corresponding to the number of blades, and these parts are then milled to the dimensions of the desired blade blank.
  • the advantage of the wide flat steels is their flexible use for a plurality of blade types and the associated savings in terms of storage costs. Due to the possibility of sawing the wide flat steel into rhomboid bars, material and machining costs are saved compared with manufacture from a standard flat steel. The fact that the machining time for sawing and milling the bars is still long, on the whole, is a drawback.
  • the basic object of the present invention is to provide a process and a blank by means of which it is possible to manufacture rhomboidal blades of axial turbo engines at a lower cost.
  • a process for manufacturing rhomboidal blades having a blade footing of a rhomboidal cross section and a blade body for axial turbo engines.
  • the process includes working the blade out of a solid blank by machining.
  • a manufactured by hot forming, hot-rolled, bar-shaped input stock is used as the starting material.
  • the cross section of the input stock has the shape of a rhomboid, which is adapted to the shape of the cross section of the rhomboidal blade footing and is larger on all sides than the maximum cross section of the blade only by the minimum oversize for machining.
  • the blank whose length corresponds to the length of the blade, optionally increased by the clamping ends necessary for the machining, is cut off from the input stock.
  • the blank is provided for manufacturing a rhomboidal blade.
  • He finished blade includes a blade footing of rhomboidal shape and a blade body for axial turbo engines and is formed by machining the bank to the finished size of the blade.
  • the blank is a bar cut off from a manufactured by hot forming hot-rolled, bar-shaped input stock.
  • the input stock has a cross section that is adapted to the cross section of the rhomboidal blade footing and is larger on all sides than the maximum cross section of the blade by only a minimum oversize for machining.
  • the input stock used in the present invention is manufactured by hot forming, such as hot rolling, precision forging, drop forging or press forging bar-shaped rolled stock of rhomboidal cross section, which is more expensive to produce than a rolled stock of rectangular cross section.
  • This input stock offers the decisive cost advantage only in the special application to the manufacture of blades to be used as rotor blades and guide vanes of axial turbo engines, because it is adapted to the rhomboidal shape of the blades. The manufacturing effort needed to bring the blade to the desired final dimension by milling from the solid is reduced as a result.
  • FIG. 1 is a front view of a rotor blade
  • FIG. 2 is a side view of the rotor blade of FIG. 1 in the direction of view A of FIG. 3;
  • FIG. 3 is a top view of the rotor blade of FIG. 1;
  • FIG. 4 is a front view of a blank for manufacturing the rotor blade according to FIGS. 1 through 3;
  • FIG. 5 is a side view of the blank of FIG. 4 in the direction of view B of FIG. 3;
  • FIG. 6 shows the top view of the blank of FIG. 4.
  • the rotor blade of a turbine or an axial compressor comprises a blade 1 of streamlined shape and a blade footing 2 .
  • the blade footing 2 has a conical shape, which is designed as a double hammerhead in the case being shown (see FIG. 1).
  • the rotor blades are held with the conical blade footings 2 in an adapted, circular groove of the rotor of the turbine, with the blade footings 2 being tightly in contact with one another.
  • the cross section of the blade footing 2 has the shape of a rhomboid or parallelogram. Instead of a rhomboid, the blade footing may also have the shape of a rhombus.
  • the largest blade cross section is obtained, in general, from the top view of the blade in all rotor blades and guide vanes of axial turbo engines.
  • the maximum cross section is formed from the largest dimensions of the blade footing 2 , the blade body 1 as well as a partially milled cover plate at the profile end on the blade head.
  • the cross section is obtained from FIG. 3 in the case of the blade being shown.
  • the guide vane of the axial turbo engine is not shown. It likewise has a streamlined blade body and a conical blade footing.
  • the blade is manufactured by working the blade shape shown in FIG. 1 from a blank 3 from the solid by machining, e.g., milling.
  • the blank 3 is shown in FIGS. 4 through 6, the contour of the blade body and of the blade footing of the blade being manufactured are indicated by the lines 1 ′ and 2 ′.
  • the blank 3 is cut off as a bar from a bar-shaped, hot-rolled input stock manufactured by hot forming.
  • the length of the blank 3 corresponds to the length of the blade or is longer than the length of the blade by the clamped ends 4 .
  • the cross-sectional shape of the bar-shaped input stock is adapted to the cross section of the blade footing 2 and it also consists of a rhomboid with the same side angles as the blade footing 2 .
  • the cross section of the rod-shaped input stock is larger on all sides than the largest cross section of the blade by only the minimum oversize 5 for machining, which is, e.g. 1 to 3 mm., or preferably about 2 mm.
  • the blank 3 is clamped into a plunging miller controlled with five NC axes.
  • this miller it is possible to completely mill the blade, i.e., the blade body 1 and the blade footing 2 , in one work mounting, with the exception of the two clamped ends 4 .
  • the machining time on the miller is reduced due to the described shape of the rhomboidal blank 3 because the machining steps that were hitherto necessary to obtain the required rhomboid in the case of the use of rectangular flat steels can be eliminated.
  • the bar-shaped input stock, from which the blank is manufactured is manufactured by hot rolling on a mill train with rollers that are calibrated corresponding to the cross-sectional shape of the blank.
  • the machine manufacturer has to order a minimum amount for manufacturing hot-rolled input stock.
  • no corresponding bar-shaped input stock can be made available by hot rolling for some blade shapes.
  • the blank is therefore manufactured from an input stock during the last shaping by drop forging or by press forging.
  • a rhomboidal bar is manufactured in a multipart hollow mold by the action of pressure. The length of the bar is coordinated with the length of the blade plus oversize for machining.
  • the shaping is performed by the stretching of the workpiece by means of a serial application of upsetting pressures with pressing strips, pressing paths or webs extending at right angles to the longitudinal axis.
  • the workpiece processed into the blank is passed uniformly through the die, which is open on both sides. Both processes are carried out by means of hammering or pressing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Forging (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
  • Non-Positive Displacement Air Blowers (AREA)
US09/904,276 2000-07-20 2001-07-12 Process and blank for preparing rhomboidal blades for axial turbo engines Abandoned US20020014006A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US10/620,033 US6910270B2 (en) 2000-07-20 2003-07-15 Process for preparing rhomboidal blades for axial turbo engines

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10035224A DE10035224A1 (de) 2000-07-20 2000-07-20 Verfahren und Rohling zum Herstellen von rhomboidischen Schaufeln für axiale Strömungsmaschinen
DEDE10035224.3 2000-07-20

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US10/620,033 Division US6910270B2 (en) 2000-07-20 2003-07-15 Process for preparing rhomboidal blades for axial turbo engines

Publications (1)

Publication Number Publication Date
US20020014006A1 true US20020014006A1 (en) 2002-02-07

Family

ID=7649536

Family Applications (2)

Application Number Title Priority Date Filing Date
US09/904,276 Abandoned US20020014006A1 (en) 2000-07-20 2001-07-12 Process and blank for preparing rhomboidal blades for axial turbo engines
US10/620,033 Expired - Lifetime US6910270B2 (en) 2000-07-20 2003-07-15 Process for preparing rhomboidal blades for axial turbo engines

Family Applications After (1)

Application Number Title Priority Date Filing Date
US10/620,033 Expired - Lifetime US6910270B2 (en) 2000-07-20 2003-07-15 Process for preparing rhomboidal blades for axial turbo engines

Country Status (9)

Country Link
US (2) US20020014006A1 (ru)
EP (1) EP1174210B1 (ru)
JP (1) JP2002138995A (ru)
AT (1) ATE293030T1 (ru)
CZ (1) CZ297900B6 (ru)
DE (2) DE10035224A1 (ru)
HU (1) HU224736B1 (ru)
PL (1) PL195318B1 (ru)
RU (1) RU2264562C2 (ru)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005024185A1 (de) * 2003-09-03 2005-03-17 Mtu Aero Engines Gmbh Verfahren zur herstellung von gasturbinenrotoren mit integraler beschaufelung
US20050186045A1 (en) * 2002-01-31 2005-08-25 Franz Killer Method and apparatus for machining a blank from all directions in a machine tool or milling machine
US7112017B2 (en) 2002-01-31 2006-09-26 Alstom Technology Ltd Method and apparatus for machining a blank from all directions
JP2015536402A (ja) * 2012-11-09 2015-12-21 メカクローム・フランスＭｅｃａｃｈｒｏｍｅ Ｆｒａｎｃｅ タービン翼を製造するための方法及び装置
US20160184940A1 (en) * 2012-12-19 2016-06-30 Mitsubishi Hitachi Power Systems, Ltd. Method for manufacturing turbine rotor blade
CN106670365A (zh) * 2016-12-27 2017-05-17 无锡透平叶片有限公司 一种大叶片锻造余量补偿方法
US9796058B2 (en) * 2013-12-20 2017-10-24 Snecma Method for producing turbine engine parts, and resulting mould and blank compromising stacked parts
US10363633B2 (en) * 2012-10-09 2019-07-30 Safran Aircraft Engines Method for manufacturing at least one metal turbine engine part
CN112959013A (zh) * 2021-03-17 2021-06-15 中国航发动力股份有限公司 一种方钢毛料叶片加工方法

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102010026784A1 (de) * 2010-07-09 2012-01-12 Kennametal Inc. Fräser, Verfahren zur Fräsbearbeitung eines Werkstücks sowie Verfahren zum Herstellen eines Fräsers
CN101987345B (zh) * 2010-08-24 2013-06-12 无锡透平叶片有限公司 汽轮机静子叶片锻件小余量设计方法
DE102010042585B4 (de) * 2010-10-18 2013-03-28 Siemens Aktiengesellschaft Verfahren zur Herstellung einer Schaufel einer Strömungsmaschine, sowie danach hergestellte Schaufel, Beschaufelung und Strömungsmaschine
CN102528138B (zh) * 2010-12-24 2014-01-08 沈阳黎明航空发动机(集团)有限责任公司 一种采用鼓形刀的复杂曲面加工方法
DE102011082850A1 (de) * 2011-09-16 2013-03-21 Siemens Aktiengesellschaft Verdichterschaufel und Verfahren zu ihrer Herstellung
JP6033668B2 (ja) * 2012-12-25 2016-11-30 三菱日立パワーシステムズ株式会社 Ｃａｍ装置及び製品形状加工方法
FR3003494B1 (fr) * 2013-03-19 2015-06-19 Snecma Brut de fonderie pour la realisation d'une aube de rotor de turbomachine et aube de rotor fabriquee a partir de ce brut
FR3015327B1 (fr) * 2013-12-20 2016-01-01 Snecma Procede de fabrication de pieces de turbomachine, ebauche et moule obtenus
CN105081710B (zh) * 2015-07-30 2017-05-03 南通中能机械制造有限公司 电机铝风叶生产工艺
CN108838629B (zh) * 2018-08-07 2021-01-22 南通中能机械制造有限公司 菱形两侧面齿形动隔叶件加工新方法
CN109623291B (zh) * 2019-01-07 2020-11-24 无锡透平叶片有限公司 一种粗加工叶片进出气边的数控编程方法
CN114043165A (zh) * 2021-07-15 2022-02-15 南通中能机械制造有限公司 一种菱形导叶片加工工艺

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US5205081A (en) * 1987-05-04 1993-04-27 Ulrich Kuehne Method for producing profiled parts by grinding and a turbomachine blade produced thereby
US5733080A (en) * 1993-09-29 1998-03-31 Siemens Aktiengesellschaft Process for milling a turbine-blade profile extending along a main axis
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US3076633A (en) * 1955-06-28 1963-02-05 Parsons & Marine Eng Turbine Turbine and like rotor blades
US2975509A (en) * 1956-05-07 1961-03-21 Cefilac Methods of extruding metals
US3045515A (en) * 1959-02-04 1962-07-24 Kralowetz Bruno Forging machine
US5205081A (en) * 1987-05-04 1993-04-27 Ulrich Kuehne Method for producing profiled parts by grinding and a turbomachine blade produced thereby
US4970887A (en) * 1988-02-03 1990-11-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Method and apparatus for upsetting forged bars
US5733080A (en) * 1993-09-29 1998-03-31 Siemens Aktiengesellschaft Process for milling a turbine-blade profile extending along a main axis
US6092408A (en) * 1997-05-12 2000-07-25 Fabris; Mario Steel mill processing by rhombic reversal reduction rolling

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20050186045A1 (en) * 2002-01-31 2005-08-25 Franz Killer Method and apparatus for machining a blank from all directions in a machine tool or milling machine
US7112017B2 (en) 2002-01-31 2006-09-26 Alstom Technology Ltd Method and apparatus for machining a blank from all directions
US7261500B2 (en) 2002-01-31 2007-08-28 Alstom Technology Ltd Method and apparatus for machining a blank from all directions in a machine tool or milling machine
US20070039179A1 (en) * 2003-09-03 2007-02-22 Mtu Aero Engines Gmbh Method for the production of gas turbine rotors having integrated blading
US7900351B2 (en) 2003-09-03 2011-03-08 Mtu Aero Engines Gmbh Method for the production of gas turbine rotors having integrated blading
WO2005024185A1 (de) * 2003-09-03 2005-03-17 Mtu Aero Engines Gmbh Verfahren zur herstellung von gasturbinenrotoren mit integraler beschaufelung
US10363633B2 (en) * 2012-10-09 2019-07-30 Safran Aircraft Engines Method for manufacturing at least one metal turbine engine part
JP2015536402A (ja) * 2012-11-09 2015-12-21 メカクローム・フランスＭｅｃａｃｈｒｏｍｅ Ｆｒａｎｃｅ タービン翼を製造するための方法及び装置
US9919392B2 (en) * 2012-12-19 2018-03-20 Mitsubishi Hitachi Power Systems, Ltd. Method for manufacturing turbine rotor blade
US20160184940A1 (en) * 2012-12-19 2016-06-30 Mitsubishi Hitachi Power Systems, Ltd. Method for manufacturing turbine rotor blade
US9796058B2 (en) * 2013-12-20 2017-10-24 Snecma Method for producing turbine engine parts, and resulting mould and blank compromising stacked parts
CN106670365A (zh) * 2016-12-27 2017-05-17 无锡透平叶片有限公司 一种大叶片锻造余量补偿方法
CN112959013A (zh) * 2021-03-17 2021-06-15 中国航发动力股份有限公司 一种方钢毛料叶片加工方法

Also Published As

Publication number Publication date
DE50105887D1 (de) 2005-05-19
JP2002138995A (ja) 2002-05-17
CZ297900B6 (cs) 2007-04-25
HUP0102889A2 (hu) 2002-05-29
US6910270B2 (en) 2005-06-28
EP1174210A3 (de) 2003-05-07
CZ20012611A3 (cs) 2002-08-14
HU0102889D0 (en) 2001-09-28
PL348790A1 (en) 2002-01-28
HUP0102889A3 (en) 2002-06-28
EP1174210B1 (de) 2005-04-13
EP1174210A2 (de) 2002-01-23
PL195318B1 (pl) 2007-08-31
ATE293030T1 (de) 2005-04-15
HU224736B1 (en) 2006-01-30
US20040020049A1 (en) 2004-02-05
RU2264562C2 (ru) 2005-11-20
DE10035224A1 (de) 2002-01-31

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