CN103452905A - Compressor - Google Patents

Compressor Download PDF

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Publication number
CN103452905A
CN103452905A CN2013102109733A CN201310210973A CN103452905A CN 103452905 A CN103452905 A CN 103452905A CN 2013102109733 A CN2013102109733 A CN 2013102109733A CN 201310210973 A CN201310210973 A CN 201310210973A CN 103452905 A CN103452905 A CN 103452905A
Authority
CN
China
Prior art keywords
mentioned
blade
wheel
contact end
compressor
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.)
Pending
Application number
CN2013102109733A
Other languages
Chinese (zh)
Inventor
长埜浩太
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 CN103452905A publication Critical patent/CN103452905A/en
Pending 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A compressor is provided that can avoid fretting damage to improve fatigue strength reliability. The present invention is characterized in that a portion on the circumferential outside and radial outside of a radial outside contact end portion 9a with a dovetail portion 4a is removed from a wheel 7. Specifically, the wheel 7 is formed with a groove portion 10 in an area that is located on the circumferential outside of the radial outside contact end portion 9a of a blade securing portion 15 with the dovetail portion 4a and that includes a radial outside of the contact end portion 9a. Rigidity on the wheel side of the contact end portion 9a between the dovetail portion 4a and the wheel 7 is reduced to reduce the occurrence of stress, thereby avoiding the lowering of fatigue life reliability resulting from fretting.

Description

Compressor
Technical field
The present invention relates to the blade embedded structure as the compressor of the element of construction of gas turbine.
Background technique
Usually, on gas turbine, be provided with for pressurized air and the compressor carried to burner.Be provided with the compressor drum around the central shaft rotation of gas turbine in the inside of compressor, the slot part on the circumference be located on the rotor wheel arranges the Embedded Division of moving vane and fixes.In addition, the relevant prior art as the fixed structure to moving vane, for example have the technology of patent documentation 1 record.
Patent documentation
Patent documentation 1: Japanese kokai publication sho 63-273000 communique
The moving vane of gas-turbine compressor in the running, centrifugal force except the generation of the weight by blade self, likely in high pressure side, it is large that pressure load becomes, owing to take the vibration force that the irregular pressure oscillation that produces in when starting is cause, vibration stress acts in blade dovetail section, causes fatigue damage.
In the past, bore its load by the blade loads supporting surface integral body of blade dovetail.But, at the blade loads supporting surface, with the end that contacts of the wheel load supporting surface of wheel, produce larger stress.This point is except producing larger stress, and also can produce to wear away is the frictionally damage of main cause, likely causes the fatigue strength reliability decrease.
Therefore, in real machine, the expectation application can obtain the blade groove structure of higher reliability.
Summary of the invention
The object of the present invention is to provide the stress that end produces that contacts that is reduced in blade and wheel, suppress the compressor of the fatigue strength reliability decrease that caused by friction.
To achieve these goals, compressor of the present invention is characterised in that, wheel from blade contact end by the part in the circumferencial direction outside until the wheel periphery is all removed.
More particularly, a kind of compressor, the moving vane that possesses the outer circumferential side that is fixed on wheel, be fixed on the stator blade of inner circumferential side of the shell of built-in above-mentioned wheel, above-mentioned moving vane has blade part, connect with the root side of this blade part and there is the platform part of the face parallel with the centrifugal loading direction of above-mentioned blade part, and dovetail section, this dovetail section is connected with this platform part, and width is widened more laterally than the parallel face of the radially inner side of above-mentioned platform part and above-mentioned platform part, this dovetail section is inserted in the blade fixed groove of the outer circumferential side that is formed on above-mentioned wheel and fixing, this compressor is characterised in that, at above-mentioned wheel, comprise and contact end more to the circumferencial direction outside than the radial outside of above-mentioned blade fixed groove and above-mentioned dovetail section, and more to the zone of radial outside, form slot part or hollow part than above-mentioned contact end.
By being above-mentioned blade groove structure, can reduce near the blade rigidity with the contact end of the wheel side that contacts end of wheel, reduce and produce stress, avoid reliability decrease fatigue life caused by friction.
Effect of the present invention is as follows.
According to the present invention, the stress that end produces that contacts that is reduced in blade and wheel can be provided, suppress the compressor of the fatigue strength reliability decrease that caused by friction.
The accompanying drawing explanation
Fig. 1 is the details drawing of the Embedded Division of embodiments of the invention one, compressor moving vane.
Fig. 2 means the figure of structure example of the gas turbine of representative.
Fig. 3 means the figure of the embedded structure of common blade.
Fig. 4 means the figure of the stress distribution produced in the structure of comparative example.
Fig. 5 has implemented the result of the mock-up fatigue test of simulation real machine load to embodiment one and comparative example.
Fig. 6 means the figure of embodiments of the invention two.
Fig. 7 means the figure of embodiments of the invention three.
Fig. 8 means the figure of embodiments of the invention four.
In figure: 1-compressor, 2-burner, 3-turbo machine, 4a-dovetail section, 4b-platform part, 5-blade loads supporting surface, 6-blade loads supporting surface equivalent stress distributes, 7-wheel, 8-wheel load supporting surface, 9a, 9b-contact end, 10,12-slot part, 11-blade rectangular portion circumferencial direction end face, 13-circle shape, 14-blade part, 15-blade fixed groove.
Embodiment
Below, use accompanying drawing explanation embodiments of the present invention.
Fig. 2 means the structure sectional view of gas turbine.Gas turbine roughly comprises compressor 1, burner 2 and turbo machine 3.The air that compressor 1 will suck from atmosphere carries out adiabatic compression as the action fluid, burner 2 is by fuel combination burning the pressurized air supplying with from compressor 1, produce the gas of High Temperature High Pressure, and turbo machine 3 when expanding, the combustion gas that import from burner 2 produces rotating power.Waste gas from turbo machine 3 is discharged into the atmosphere.
Fig. 3 means the figure of the blade groove structure of common compressor.In the structure of Fig. 3, by blade loads supporting surface 5 integral body of the 4a of dovetail section bear centrifugal force that the weight by blade part 14 self produces, with take the relevant load of the irregular pressure oscillation of generation is cause when the starting vibration force.But, from the distribution 6 of the blade loads supporting surface equivalent stress shown in Fig. 4, can find out, produce larger stress at blade loads supporting surface 5 with the end that contacts of the wheel load supporting surface 8 of wheel 7.This point is except producing larger stress, and also producing to wear away is the frictionally damage of main cause, likely causes the fatigue strength reliability decrease.
Therefore, in the present invention, wheel 7, comprise than the radial outside of blade fixed groove 15 and the 4a of dovetail section contact end by the circumferencial direction outside (the width direction outside of par 4b), and form slot part or hollow part than the contact end by the zone of radial outside.Below, this object lesson is described.
(embodiment one)
Fig. 1 is as embodiments of the invention one, and expression can show the figure of the turbine bucket groove structure of feature of the present invention.As shown in the figure, as the structure of the root of blade, by the platform part 4b with face parallel with the centrifugal loading direction of blade, more form to wheel radially inner side and the 4a of dovetail section that widens more laterally than parallel portion than this platform part 4b.And, the embedding part at wheel 7 with the 4a of dovetail section of compressor blade, wheel 7, comprise than with the 4a(of dovetail section blade) radial outside contact end 9a by the circumferencial direction outside and than contact end 9a the region division slot part 10 by radial outside.This slot part 10 by than contact end 9a more towards the first line part 10a in the circumferencial direction outside, more form to the second line part 10b of wheel peripheral direction and the curve part 10c that links these straight lines than this line part 10a.In addition, slot part 10 expectations are formed on the zone that end 9b leans on the circumferencial direction inboard that contacts comprised than the radially inner side with the 4a of dovetail section.According to this structure, by the contact jaw rigidity that makes wheel, descend, can reduce the stress of contact end 9a.
Fig. 5 has meaned to implement the result of simulation in the mock-up fatigue test of the pattern of the blade slot part generation centrifugal force of the present embodiment structure and comparative example structure.Test result is used result the nondimensionalization of comparative example structure.According to this result, by using the present embodiment structure, with the shape of comparative example, compare, approximately improve six times fatigue life.
(embodiment two)
Fig. 6 means embodiments of the invention two.It is characterized in that, with wheel from blade contact end 9 to the wheel profile, become large mode with the distance of blade rectangular portion circumferencial direction end face 11, to the circumferencial direction outside, remove until the part of above-mentioned wheel periphery.Thus, with embodiment one, compare, near the intensity that can suppress wheel and surface of contact blade descends.
(embodiment three)
Fig. 7 means embodiments of the invention three.By the slot part 12 formed by the straight line parallel with blade loads supporting surface 5 and the straight line that extends to wheel profile direction from the two end part of this straight line is set, can reduce wheel side opening section, and can eliminate, thereby can reduce the mobile impact on turbo machine action fluid.
(embodiment four)
Fig. 8 means embodiments of the invention four.Zone in the outer shape direction of the surface of contact than wheel and blade forms hollow part.As hollow part, for example by circle or elliptical aperture as shown in Figure 8 is set in the axial direction, identical with embodiment three, reduce the stress of contact end, and can suppress the impact on turbo machine action fluid.
In the various embodiments described above, consider the contact end 9a distortion by wheel, realize the reduction of stress.Therefore, expect that the position of these slot parts and hollow part (hole) is positioned at the radially top of surface of contact.But the suitably setting such as the load condition of real machine, the intensity of suitable material need to be considered in the size of these slot parts, hollow part, position.
In addition, as the fatigue strength raising method in the zone that reduces these rigidity, can enumerate the surface modification that applies or produced by friction stir of the compressive residual stress produced by shot peening, injection sclerosis etc.

Claims (6)

1. a compressor, possess the outer circumferential side that is fixed on wheel moving vane, be fixed on the stator blade of inner circumferential side of the shell of built-in above-mentioned wheel,
Above-mentioned moving vane has blade part, with the root side of this blade part, connects and have platform part and the dovetail section of the face parallel with the centrifugal loading direction of above-mentioned blade part, this dovetail section is connected with this platform part, and width is widened more laterally than the parallel face of the radially inner side of above-mentioned platform part and above-mentioned platform part, this dovetail section is inserted in the blade fixed groove of the outer circumferential side that is formed on above-mentioned wheel and fixing
This compressor is characterised in that,
Above-mentioned wheel, comprise than above-mentioned blade fixed groove and more to the circumferencial direction outside and than above-mentioned contact end, more to the zone of radial outside, form slot part or hollow part with the end that contacts of the radial outside of above-mentioned dovetail section.
2. compressor according to claim 1, is characterized in that,
Above-mentioned slot part or hollow part be formed on above-mentioned wheel, comprise and contact end more to the zone of circumferencial direction inboard than the radially inner side of above-mentioned blade fixed groove and above-mentioned dovetail section.
3. compressor according to claim 1, is characterized in that,
Above-mentioned slot part is by from above-mentioned contact end towards first line part in the circumferencial direction outside, form towards the second line part of radial outside and the curve part that links above-mentioned first and second line part.
4. compressor according to claim 1, is characterized in that,
Above-mentioned slot part forms, along with from above-mentioned contact end towards radial outside, become large with the distance of the parallel face of above-mentioned par.
5. compressor according to claim 1, is characterized in that,
Apply at above-mentioned slot part or hollow part the compressive residual stress produced by shot peening.
6. compressor according to claim 1, is characterized in that,
Surface portion at above-mentioned slot part or hollow part carries out the surface modification of being undertaken by friction stir.
CN2013102109733A 2012-05-31 2013-05-31 Compressor Pending CN103452905A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2012123885A JP2013249756A (en) 2012-05-31 2012-05-31 Compressor
JP2012-123885 2012-05-31

Publications (1)

Publication Number Publication Date
CN103452905A true CN103452905A (en) 2013-12-18

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ID=48534257

Family Applications (1)

Application Number Title Priority Date Filing Date
CN2013102109733A Pending CN103452905A (en) 2012-05-31 2013-05-31 Compressor

Country Status (4)

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

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6785555B2 (en) * 2016-01-15 2020-11-18 三菱パワー株式会社 How to assemble the rotor blade to the turbine rotor
US11021972B2 (en) 2018-08-14 2021-06-01 Rolls-Royce North American Technologies Inc. Variable pitch blade holder for gas turbine engine
CN111563317B (en) * 2020-04-14 2023-06-16 中国北方车辆研究所 Shot peening strengthening evaluation method for floating support friction plate

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH430754A (en) * 1964-01-10 1967-02-28 Goerlitzer Maschinenbau Veb Method for fastening the blades of axial turbo machines, in particular blades manufactured with coarser root tolerances
JPS58167807A (en) * 1982-03-29 1983-10-04 Hitachi Ltd Blade installation structure of turbo-machinery
JPS63273000A (en) * 1987-04-30 1988-11-10 Toshiba Corp Impeller of compressor
US6183202B1 (en) * 1999-04-30 2001-02-06 General Electric Company Stress relieved blade support
US20030123986A1 (en) * 2001-11-22 2003-07-03 Snecma Moteurs Device for immobilizing blades in a slot of a disk
CN1869408A (en) * 2005-05-24 2006-11-29 通用电气公司 Coated forward stub shaft dovetail slot
CN101046160A (en) * 2006-03-31 2007-10-03 通用电气公司 Hybrid bucket dovetail pocket design for mechanical retainment
US20080298972A1 (en) * 2007-01-18 2008-12-04 Snecma Rotor disk for turbomachine fan

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GB1151937A (en) * 1966-08-26 1969-05-14 Mini Of Technology Bladed Rotors for Fluid Flow Machines
JPS6065204A (en) * 1983-09-19 1985-04-15 Toshiba Corp Embedded coupling device for turbine vane
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
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 (en) * 2005-05-12 2012-04-18 通用电气公司 Ultrasonic peening treatment of assembled components
US7516547B2 (en) * 2005-12-21 2009-04-14 General Electric Company Dovetail surface enhancement for durability
US8899933B2 (en) * 2012-01-03 2014-12-02 General Electric Company Rotor blade mounting

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH430754A (en) * 1964-01-10 1967-02-28 Goerlitzer Maschinenbau Veb Method for fastening the blades of axial turbo machines, in particular blades manufactured with coarser root tolerances
JPS58167807A (en) * 1982-03-29 1983-10-04 Hitachi Ltd Blade installation structure of turbo-machinery
JPS63273000A (en) * 1987-04-30 1988-11-10 Toshiba Corp Impeller of compressor
US6183202B1 (en) * 1999-04-30 2001-02-06 General Electric Company Stress relieved blade support
US20030123986A1 (en) * 2001-11-22 2003-07-03 Snecma Moteurs Device for immobilizing blades in a slot of a disk
CN1869408A (en) * 2005-05-24 2006-11-29 通用电气公司 Coated forward stub shaft dovetail slot
CN101046160A (en) * 2006-03-31 2007-10-03 通用电气公司 Hybrid bucket dovetail pocket design for mechanical retainment
US20080298972A1 (en) * 2007-01-18 2008-12-04 Snecma Rotor disk for turbomachine fan

Also Published As

Publication number Publication date
JP2013249756A (en) 2013-12-12
US20130323039A1 (en) 2013-12-05
EP2669478A1 (en) 2013-12-04

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Owner name: MITSUBISHI HITACHI POWER SYSTEM LTD.

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Effective date: 20141204

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Applicant after: Mitsubishi Hitachi Power System Ltd.

Address before: Tokyo, Japan, Japan

Applicant before: Hitachi Ltd.

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Application publication date: 20131218