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EP2669478A1 - Verdichter - Google Patents

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Publication number
EP2669478A1
EP2669478A1 EP13169807.8A EP13169807A EP2669478A1 EP 2669478 A1 EP2669478 A1 EP 2669478A1 EP 13169807 A EP13169807 A EP 13169807A EP 2669478 A1 EP2669478 A1 EP 2669478A1
Authority
EP
European Patent Office
Prior art keywords
blade
wheel
contact end
groove
radial outside
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Withdrawn
Application number
EP13169807.8A
Other languages
English (en)
French (fr)
Inventor
Kota Nagano
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.)
Mitsubishi Power Ltd
Original Assignee
Hitachi Ltd
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 Hitachi Ltd filed Critical Hitachi Ltd
Publication of EP2669478A1 publication Critical patent/EP2669478A1/de
Withdrawn legal-status Critical Current

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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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/294—Three-dimensional machined; miscellaneous grooved
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
    • 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 present invention relates to a blade-implanting structure for a compressor that is a constituent element of a gas turbine.
  • Gas turbines generally have a compressor to compress and deliver air to a combustor.
  • the compressor is internally provided with a compressor rotor rotating around a central axis of a gas turbine.
  • an implanting portion of a rotor blade is fixedly fitted into a circumferential groove portion provided on a rotor wheel.
  • a conventional technique relating to the rotor blade securing structure is described in e.g. JP-63-273000-A .
  • the rotor blade of the gas turbine compressor While the gas turbine operates, the rotor blade of the gas turbine compressor is subjected to centrifugal force caused by its own weight and to a large pressure load on its high-pressure side. In addition, vibration stress acts on the dovetail portion of the blade due to the exciting force caused by irregular pressure variations that occur during start-up. As a result, fatigue damage may result.
  • the compressor according to the present invention is characterized in that a portion on the circumferential outside and radial outside of a contact end portion with a blade is removed from a wheel.
  • the compressor includes a rotor blade secured to an outer circumferential side of a wheel and a stator blade secured to an inner circumferential side of a casing incorporating the wheel.
  • the rotor blade includes a blade portion, a platform portion joined to a root side of the blade portion and having planes parallel to a centrifugal-force load direction of the blade portion, and a dovetail portion which merges with the platform portion, is located radially inward of the platform portion and is increased in width outwardly from the parallel planes of the platform portion.
  • the dovetail portion is fixedly inserted into a blade securing groove formed on the outer circumferential side of the wheel.
  • the wheel is formed with a groove portion or a hollow portion in an area that is located on a circumferential outside of a radial outside contact end portion of the blade securing groove with the dovetail portion and that includes a radial outside of the radial outside contact end portion.
  • the present invention can provide the compressor that can reduce stress occurring at the contact end portion between the wheel and the blade to suppress the lowering of fatigue strength reliability resulting from fretting.
  • Fig. 2 is a configurational cross-sectional view of a gas turbine.
  • a gas turbine is mainly composed of a compressor 1, a combustor 2 and a turbine 3.
  • the compressor 1 adiabatically compresses, as working fluid, air sucked from the atmosphere.
  • the combustor 2 mixes fuel with the compressed air delivered from the compressor 1 and burns the mixture to produce high temperature and high pressure air.
  • the turbine 3 generates rotational power when the combustion gas introduced from the combustor 2 expands.
  • the exhaust gas from the turbine 3 is discharged into the atmosphere.
  • the compressor 1 includes a rotor blade 1b secured to an outer circumferential side of a wheel 7 (shown in fig. 3 described later), a casing 1a incorporating the wheel 7, and a stator blade 1c secured to an inner circumferential side of the casing 1a.
  • Fig. 3 illustrates a blade-groove structure of a common compressor as a comparative example.
  • This fig. 3 is an enlarged diagram that shows an installation state of the rotor blade 1b shown in fig. 2 .
  • the rotor blade 1b includes a blade portion 14, a platform portion 4b joined to a root side (lower side in Fig. 3 ) of the blade portion 14, and a dovetail portion 4a fixedly inserted into a blade securing groove 15 formed on the outer circumferential side (upper side in Fig. 3 ) of the wheel 7.
  • a groove portion or a hollow portion described later is not formed in the wheel 7.
  • a blade-load-receiving surface 5 of the dovetail portion 4a wholly bears centrifugal force caused by its own weight of the blade portion 14 and a load relating to exciting force caused by irregular pressure variations that occur during the start-up.
  • high stress occurs at a radial outside contact end portion 9a between the blade-load-receiving surface 5 and a wheel load receiving surface 8 of the wheel 7. Since such a contact end portion 9a suffers fretting damage resulting from abrasion in addition to high stress, reliability in fatigue strength is likely to lower.
  • a wheel 7 is formed with a groove portion or a hollow portion formed in an area that is located on a circumferential outside (a widthwise outside of a platform portion 4b) of a radial outside contact end portion 9a of a blade securing groove 15 with a dovetail portion 4a and that includes a radial outside of the contact end portion 9a.
  • a circumferential outside a widthwise outside of a platform portion 4b
  • a radial outside contact end portion 9a of a blade securing groove 15 with a dovetail portion 4a and that includes a radial outside of the contact end portion 9a.
  • Fig. 1 illustrates a blade groove structure of a compressor that exhibits the most characteristic feature of the present invention, as a first embodiment of the present invention.
  • a root portion of a rotor blade is formed to have a platform portion 4b having planes 11 (circumferential end faces) parallel to a centrifugal-force load direction of the blade (an upward direction in Fig.1 ) and a dovetail portion 4a flaring radially inward of the wheel (toward a lower side in Fig. 1 ) from the platform portion 4b and outwardly from the parallel planes 11 (in a left-right direction in Fig. 1 ).
  • a groove portion 10 is provided in an area that is located on the circumferential outside (the outside of left-right direction in Fig. 1 ) of a radial outside contact end portion 9a of the wheel 7 with the dovetail portion 4a (the blade) and that includes the radial outside (the upper side in Fig. 1 ) of the contact end portion 9a.
  • the groove portion 10 includes a first straight-line part 10a extending toward the circumferential outside from the contact end portion 9a, a second straight-line part 10b extending toward the radial outside from the straight-line part 10a, and a curve part 10c connecting these straight-line parts together.
  • the groove portion 10 be formed in an area including the circumferential inside (the inside of left-right direction in Fig. 1 ) of a radial inside contact end portion 9b with the dovetail portion 4a.
  • Fig. 5A is a graph showing the results of mock-up fatigue tests simulating centrifugal force occurring at the blade groove portion of each of the structures of the present embodiment ( Fig. 5C ) and a comparative example ( Fig. 5B ). Test results are made dimensionless using the results of the structure of the comparative example. The present results show that the use of the structure of the present embodiment improves a fatigue life about six times that of the shape of the comparative example.
  • a second embodiment of the present invention is shown in Fig. 6 .
  • the second embodiment is characterized in that a portion extending from a radial outside contact end portion 9a to the outer circumference of a wheel 7 is removed from the wheel 7 so as to gradually increase a circumferential distance from a circumferential end face 11 of a platform portion 4b of a rotor blade as it goes toward the radial outside of the wheel (upward in Fig. 6 ) from the contact end portion 9a with a dovetail portion 4a of a rotor blade, thereby providing a groove portion 10 in the wheel 7.
  • This can suppress the lowering of strength at a position close to the contact surface of the wheel with the blade compared with that of the first embodiment.
  • a third embodiment of the present invention is shown in Fig. 7 .
  • a groove portion 12 of a wheel 7 is provided that is formed by a straight line parallel to a blade load-receiving surface 5 and straight lines extending from both respective ends thereof toward the radial outside of the wheel. This can make a wheel-side opening portion small or eliminate it, thereby making it possible to reduce an influence on the flow of turbine working fluid.
  • a fourth embodiment of the present invention is described in Fig. 8 .
  • a hollow portion 13 of a wheel 7 is formed in an area that is located on a radial outside of a contact surface between the wheel and a dovetail portion 4a of a rotor blade.
  • a circular or elliptical hole as shown in Fig. 8 is provided as the hollow portion 13.
  • the deformation of the contact end portion 9a of the wheel can achieve a reduction in stress. It is desirable, therefore, that the groove and the hollow portion (the hole) be located radially above the contact surface. However, it is necessary to appropriately set the size and position of the groove portion or the hollow portion taking into consideration the load conditions of an actual machine, the strength of material to be applied and the like.
  • Methods of increasing the fatigue strength of the area having reduced rigidity include application of compressive residual stress by shot peening or water jet peening and surface modification by friction stir.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13169807.8A 2012-05-31 2013-05-29 Verdichter Withdrawn EP2669478A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP2012123885A JP2013249756A (ja) 2012-05-31 2012-05-31 圧縮機

Publications (1)

Publication Number Publication Date
EP2669478A1 true EP2669478A1 (de) 2013-12-04

Family

ID=48534257

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13169807.8A Withdrawn EP2669478A1 (de) 2012-05-31 2013-05-29 Verdichter

Country Status (4)

Country Link
US (1) US20130323039A1 (de)
EP (1) EP2669478A1 (de)
JP (1) JP2013249756A (de)
CN (1) CN103452905A (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3611386A3 (de) * 2018-08-14 2020-05-27 Rolls-Royce North American Technologies, Inc. Haltevorrichtung für turbofanschaufel mit variablem anstellwinkel für turbostrahltriebwerke
CN111563317A (zh) * 2020-04-14 2020-08-21 中国北方车辆研究所 一种浮动支撑摩擦片喷丸强化评估方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6785555B2 (ja) * 2016-01-15 2020-11-18 三菱パワー株式会社 動翼のタービンロータへの組付方法

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH430754A (de) * 1964-01-10 1967-02-28 Goerlitzer Maschinenbau Veb Verfahren zur Befestigung der Schaufeln von Axialturbomaschinen, insbesondere von mit gröberen Fusstoleranzen hergestellten Schaufeln
JPS58167807A (ja) * 1982-03-29 1983-10-04 Hitachi Ltd タ−ボ機械のブレ−ド取付構造
JPS63273000A (ja) 1987-04-30 1988-11-10 Toshiba Corp 圧縮機動翼
EP1314856A1 (de) * 2001-11-22 2003-05-28 Snecma Moteurs Vorrichtung zur Sicherung von Laufschaufeln in einer Nut einer Rotorscheibe
EP2612999A2 (de) * 2012-01-03 2013-07-10 General Electric Company Schaufelmontagesystem

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1151937A (en) * 1966-08-26 1969-05-14 Mini Of Technology Bladed Rotors for Fluid Flow Machines
JPS6065204A (ja) * 1983-09-19 1985-04-15 Toshiba Corp タ−ビン羽根の植込結合装置
US5310317A (en) * 1992-08-11 1994-05-10 General Electric Company Quadra-tang dovetail blade
US5735671A (en) * 1996-11-29 1998-04-07 General Electric Company Shielded turbine rotor
US6183202B1 (en) * 1999-04-30 2001-02-06 General Electric Company Stress relieved blade support
GB2380770B (en) * 2001-10-13 2005-09-07 Rolls Royce Plc Indentor arrangement
US6945754B2 (en) * 2003-05-29 2005-09-20 General Electric Company Methods and apparatus for designing gas turbine engine rotor assemblies
CN101175606B (zh) * 2005-05-12 2012-04-18 通用电气公司 超声波喷丸处理系统及方法
US7217099B2 (en) * 2005-05-24 2007-05-15 General Electric Company Coated forward stub shaft dovetail slot
US7516547B2 (en) * 2005-12-21 2009-04-14 General Electric Company Dovetail surface enhancement for durability
US7942639B2 (en) * 2006-03-31 2011-05-17 General Electric Company Hybrid bucket dovetail pocket design for mechanical retainment
FR2911632B1 (fr) * 2007-01-18 2009-08-21 Snecma Sa Disque de rotor de soufflante de turbomachine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH430754A (de) * 1964-01-10 1967-02-28 Goerlitzer Maschinenbau Veb Verfahren zur Befestigung der Schaufeln von Axialturbomaschinen, insbesondere von mit gröberen Fusstoleranzen hergestellten Schaufeln
JPS58167807A (ja) * 1982-03-29 1983-10-04 Hitachi Ltd タ−ボ機械のブレ−ド取付構造
JPS63273000A (ja) 1987-04-30 1988-11-10 Toshiba Corp 圧縮機動翼
EP1314856A1 (de) * 2001-11-22 2003-05-28 Snecma Moteurs Vorrichtung zur Sicherung von Laufschaufeln in einer Nut einer Rotorscheibe
EP2612999A2 (de) * 2012-01-03 2013-07-10 General Electric Company Schaufelmontagesystem

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3611386A3 (de) * 2018-08-14 2020-05-27 Rolls-Royce North American Technologies, Inc. Haltevorrichtung für turbofanschaufel mit variablem anstellwinkel für turbostrahltriebwerke
US11021972B2 (en) 2018-08-14 2021-06-01 Rolls-Royce North American Technologies Inc. Variable pitch blade holder for gas turbine engine
CN111563317A (zh) * 2020-04-14 2020-08-21 中国北方车辆研究所 一种浮动支撑摩擦片喷丸强化评估方法

Also Published As

Publication number Publication date
JP2013249756A (ja) 2013-12-12
US20130323039A1 (en) 2013-12-05
CN103452905A (zh) 2013-12-18

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