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WO2006117847A1 - Micro turbine a gaz - Google Patents

Micro turbine a gaz Download PDF

Info

Publication number
WO2006117847A1
WO2006117847A1 PCT/JP2005/008016 JP2005008016W WO2006117847A1 WO 2006117847 A1 WO2006117847 A1 WO 2006117847A1 JP 2005008016 W JP2005008016 W JP 2005008016W WO 2006117847 A1 WO2006117847 A1 WO 2006117847A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
micro gas
gas turbine
wheel
turbine wheel
Prior art date
Application number
PCT/JP2005/008016
Other languages
English (en)
Japanese (ja)
Inventor
Kouta Nagano
Masaru Sekihara
Yasushi Hayasaka
Manabu Yagi
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.
Priority to PCT/JP2005/008016 priority Critical patent/WO2006117847A1/fr
Priority to JP2007514418A priority patent/JPWO2006117847A1/ja
Publication of WO2006117847A1 publication Critical patent/WO2006117847A1/fr

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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
    • F01D5/063—Welded rotors
    • 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
    • F05D2250/80—Size or power range of the machines
    • F05D2250/82—Micromachines

Definitions

  • the present invention relates to a micro gas turbine, and more particularly to a micro gas turbine in which a turbine rotor is devised.
  • the turbine wheel diameter of a turbine turbine used is also increasing in diameter.
  • the temperature of the combustion gas supplied to the micro gas turbine also tends to rise in response to high efficiency, so the material used for the turbine wheel is a nickel-base alloy material with excellent high-temperature strength. It is used.
  • the nickel-base alloy material has poor machinability, the turbine wheel is formed by forging the nickel-base alloy material, and the turbine wheel is connected to the turbine shaft to form a turbine rotor.
  • Patent Document 1 A turbine rotor of a micro gas turbine in which a turbine wheel and a turbine shaft are connected has already been proposed in Patent Document 1, for example.
  • Patent Document 1 Japanese Patent Application Laid-Open No. 2002-235547
  • the position of the pouring gate in the hot water of the turbine bin wheel is almost always provided at one end in the axial direction at the radial center of the turbine wheel in consideration of penetration and solidification.
  • the generation positions are also concentrated on one end side in the axial direction at the radial center of the turbine wheel.
  • An object of the present invention is to provide a micro gas turbine capable of maintaining fatigue strength even if a forging defect exists in a turbine wheel manufactured by forging a nickel-base alloy material.
  • the present invention provides fatigue by providing a hollow portion or applying a residual compressive stress at the radial center of a turbine wheel manufactured by forging a nickel-base alloy material.
  • Strength maintenance means were provided.
  • FIG. 1 is a partially longitudinal side view showing a turbine rotor of a micro gas turbine according to the present invention.
  • FIG. 2 is a block diagram showing a micro gas turbine power generation facility using the micro gas turbine of FIG.
  • FIG. 3 is a view corresponding to FIG. 1 and showing a first modification of the turbine rotor of the micro gas turbine according to the present invention.
  • FIG. 4 is a diagram showing a second modification of the turbine rotor of the micro gas turbine according to the present invention. Equivalent figure.
  • FIG. 5 is a view corresponding to FIG. 1, showing a third modification of the turbine rotor of the micro gas turbine according to the present invention.
  • FIG. 6 is a view corresponding to FIG. 1 and showing a fourth modification of the turbine rotor of the micro gas turbine according to the present invention.
  • FIG. 7 is a view corresponding to FIG. 1, showing a fifth modification of the turbine rotor of the micro gas turbine according to the present invention.
  • the micro gas turbine power generation facility to which the micro gas turbine 1 according to the present invention is applied is connected so that the micro gas turbine 1, the compressor 2, and the generator 3 are coaxial. ing. Then, the outside air a is compressed by the compressor 2 and discharged as compressed air b. The compressed air b discharged from the compressor 2 is passed through the regenerative heat exchange 4 in order to raise the temperature, and the heated compressed air c raised in temperature is supplied into the combustor 5. The heated compressed air c supplied into the combustor 5 is mixed with fuel supplied from a fuel supply device (not shown) and burned. The combustion gas d from the combustor 5 is supplied to the micro gas turbine 1 to rotate the turbine port 8.
  • the exhaust gas e after driving the turbine rotor 8 of the micro gas turbine 1 raises the temperature of the compressed air b discharged from the compressor 2 in the regeneration heat exchanger 4 and then is discharged.
  • the turbine rotor 8 of the micro gas turbine 1 is driven, for example, a permanent magnet type rotor of the generator 3 is driven and power generation is started.
  • the generated power is supplied to a load (not shown) via the rectifier 6 and the inverter 7.
  • the single-bin rotor 8 includes a turbine wheel 9 and a turbine shaft 10 connected to the turbine wheel 9, and the turbine wheel 9 is formed by forging a nickel-based alloy material.
  • the turbine wheel 9 formed by forging a nickel-based alloy material has a through hole 11 that is a hollow portion at the center in the radial direction so as to be concentric with the turbine shaft 10 over the entire axial length.
  • This through hole 11 may be formed by placing the core at a position that becomes the axial center of the turbine wheel 9 during the fabrication of the nickel-based alloy material, pouring the core, and removing the core after solidification. Although it is not workable, it may be formed by cutting with a machine tool. Note that when the through hole 11 is provided over the entire length of the turbine wheel 9, the pouring gate for the nickel-base alloy material may be provided either in the axial direction, but the condensation after pouring is considered. Then, it is desirable to provide the turbine shaft 10 on the side opposite to the turbine blade 9W and the connecting portion side.
  • a connecting end 10C of the turbine shaft 10 is connected to one end of the turbine wheel 9 thus formed, for example, the end opposite to the turbine blade 9W, by a well-known connection such as friction welding or welding.
  • the turbine rotor 8 is formed by connecting by means.
  • a reliable and economical friction press connection is desirable.
  • the defect may be scraped off with a lathe or the like. At that time, it is necessary to devise measures such as cutting in a curved line so that the stress does not concentrate on the part removed.
  • the turbine rotor 8 is configured as described above, even if a forging defect occurs when a large-diameter turbine wheel having an outer diameter exceeding about 200 mm is formed by forging a nickel-based alloy material, the through hole 11 is formed.
  • the forged defects which cause a reduction in fatigue strength, can be removed, the decrease in fatigue strength as the turbine wheel 9 can be prevented.
  • the turbine wheel 9 can be reduced in weight, and the through hole 11 exhibits a heat insulating action, so that the heat of the surface of the turbine wheel 9 exposed to high temperature can be reduced. It becomes difficult to transmit to the turbine shaft 10, and the heat around the shaft can be protected.
  • FIG. 3 shows a first modification of the turbine rotor 8 of the micro gas turbine according to the present invention.
  • the same reference numerals as those in FIG. 1 denote the same components, and thus detailed description thereof is omitted.
  • FIG. 1 what is different from Fig. 1 is a connection configuration of the turbine wheel 9 and the turbine shaft 10. That is, in FIG. 1, the turbine wheel 9 and the connecting end 10C of the turbine shaft 10 are connected by friction welding or the like, but in the first modification, the end of the turbine wheel 9 of the turbine shaft 10 is connected.
  • a wheel receiving portion 12 is provided at a portion facing the portion, and a bolt 13 that penetrates the through hole 11 of the turbine wheel 9 from the wheel receiving portion 12 is provided.
  • the nut 14 is screwed into the through end of the bolt 13 that has passed through the through hole 11 and tightened, whereby the turbine wheel 9 is fastened by the wheel receiving portion 12 and the nut 14 and both are connected.
  • FIG. 4 shows a second modification of the turbine rotor 8 of the micro gas turbine according to the present invention.
  • the difference from FIGS. 1 and 3 is that the axis of the turbine wheel 9 that does not pass through the through hole 11.
  • a concentric bottomed hole (hollow part) 15 was provided.
  • the connection between the turbine shaft 10 and the turbine wheel 9 is the same as that of the turbine rotor 8 shown in FIG.
  • the bottomed hole 15 is provided at the end of the turbine wheel 9 on the side of the turbine wheel 9 that is connected to the turbine shaft 10 so as to extend toward the turbine blade 9W side. A certain force The bottomed hole 15 is provided at this position because the pouring gate for nickel-base alloy material is provided on the side away from the turbine blade 9W, so that the turbine blade 9W is not affected by condensation during solidification. In the present invention, it is assumed that the pouring gate for the nickel base alloy material is formed near the radial center of the turbine wheel 9 on the anti-turbine blade 9W side. .
  • FIG. 5 shows a third modification of the turbine rotor 8 of the micro gas turbine according to the present invention.
  • an arc-shaped receiving hole (hollow part) 16 concentric with the shaft core is provided at the connecting portion of the turbine wheel 9 with the turbine shaft 10, and a hemisphere is formed at the end of the opposing turbine shaft 10.
  • a connecting projection 17 is provided. Then, after inserting and positioning the connecting projection 17 of the turbine shaft 10 into the receiving hole 16 of the turbine wheel 9, the receiving hole 16 and the connecting projection 17 are connected by friction welding.
  • the receiving hole 16 and the connecting projection 17 may be formed to have the same curvature. However, for efficiency, the curvature of both may be changed in order to perform friction welding. ,.
  • the forging defect generated at the center in the radial direction of the turbine wheel 9 can be removed by providing the receiving hole 16 in the same manner as the turbine rotor 8 shown in FIG. It is possible to prevent the fatigue strength from being lowered.
  • FIG. 6 shows a fourth modification of the turbine rotor 8 of the micro gas turbine according to the present invention.
  • a difference from the third modification shown in FIG. 5 is that a tip hole 18 is provided at the tip of the connecting projection 17.
  • the tip hole 18 is provided in addition to the same effect as the third modification shown in FIG. 5, so that heat transfer from the turbine wheel 9 can be suppressed by the tip hole 18. Furthermore, since the space portion by the tip hole 18 exists in the turbine wheel 9, the turbine rotor 8 can be reduced in weight. Furthermore, the presence of the space by the tip hole 18 makes it possible to minimize the friction welding area of the connecting projection 17 with respect to the receiving hole 16. The driving force at the time of friction welding can be reduced.
  • the turbine rotor 8 shown in FIGS. 1 to 6 is formed by actively forming a space portion in the radial center portion of the turbine wheel 9, so This eliminates the forging defects that occur easily and eliminates the decrease in fatigue strength.
  • the nickel-base alloy material is not excellent in mechanical caulking properties, a mechanical force such as a hollow portion is formed on the turbine wheel 9 formed by forging the -kel-base alloy material. It is troublesome to apply.
  • the fifth modification of the turbine rotor 8 of the micro gas turbine according to the present invention shown in FIG. 7 suppresses the decrease in fatigue strength due to forging defects without performing machining.
  • the decrease in fatigue strength due to the forging defects of the turbine wheel 9 is suppressed by performing heat treatment.
  • the radial center of the turbine wheel 9, in particular, the portion other than the portion where the turbine shaft 10 is connected, in other words, the portion on the side where the hot water pouring gate is provided, is heated, and then the turbine shaft The part where 10 is connected is cooled rapidly.
  • heat treatment initially, tensile stress due to thermal stress is generated at the site where the turbine shaft 10 is connected, and it remains as a residual compressive stress by rapid cooling, which gives residual compressive stress. Part 19 is formed.
  • the fatigue strength of a metal material is improved by applying residual compressive stress, the same fatigue treatment is applied to the turbine wheel 9 whose fatigue strength is reduced due to forging defects.
  • the strength can be improved, and as a result, even if forged defects exist, the decrease in fatigue strength can be suppressed and maintained.
  • the turbine shaft 10 is connected by a known connecting means to form the turbine rotor 8. If the fatigue strength of the residual compressive stress imparting portion 19 cannot be improved by friction welding or welding with heat as a connecting means, the turbine shaft 10 is connected by friction welding or welding before heat treatment of the turbine wheel 9. Connect it in advance!
  • the decrease in fatigue strength due to forging defects caused by machining such as forming a hollow portion in the turbine wheel 9 is suppressed and maintained. be able to.
  • the present invention is essential for a forged turbine wheel made of a nickel-based alloy material that increases in size as the output of a micro gas turbine increases.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Forging (AREA)

Abstract

Micro turbine à gaz qui même lorsqu'un défaut de moulage existe dans une roue de turbine produite par le moulage d'un matériau d'alliage à base de nickel, est capable de maintenir sa résistance à la fatigue. Pour obtenir une telle micro turbine à gaz, la roue de turbine produite par le moulage d'un matériau d'alliage à base de nickel dans son centre diamétral est dotée de moyens de maintien de la résistance à la fatigue en disposant une partie creuse ou par une application de contraintes de compression résiduelle.
PCT/JP2005/008016 2005-04-27 2005-04-27 Micro turbine a gaz WO2006117847A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/JP2005/008016 WO2006117847A1 (fr) 2005-04-27 2005-04-27 Micro turbine a gaz
JP2007514418A JPWO2006117847A1 (ja) 2005-04-27 2005-04-27 マイクロガスタービン

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/JP2005/008016 WO2006117847A1 (fr) 2005-04-27 2005-04-27 Micro turbine a gaz

Publications (1)

Publication Number Publication Date
WO2006117847A1 true WO2006117847A1 (fr) 2006-11-09

Family

ID=37307654

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/JP2005/008016 WO2006117847A1 (fr) 2005-04-27 2005-04-27 Micro turbine a gaz

Country Status (2)

Country Link
JP (1) JPWO2006117847A1 (fr)
WO (1) WO2006117847A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101596665B (zh) * 2008-06-03 2012-01-18 中国兵器工业集团第七○研究所 一种钛铝合金涡轮转轴三体结构连接的工艺方法
JP2013170487A (ja) * 2012-02-20 2013-09-02 Ihi Corp 過給機
CN104246167A (zh) * 2012-05-03 2014-12-24 博格华纳公司 减小应力的超级背板叶轮
WO2018181085A1 (fr) * 2017-03-30 2018-10-04 三菱重工コンプレッサ株式会社 Procédé de fabrication de rotor, turbine et machine de rotation

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5896101A (ja) * 1981-12-03 1983-06-08 Honda Motor Co Ltd タ−ビンホイ−ルの製造方法
JPH05212493A (ja) * 1992-02-06 1993-08-24 Mitsubishi Heavy Ind Ltd 精密鋳造翼の製造方法
JPH06229203A (ja) * 1993-02-01 1994-08-16 Daido Steel Co Ltd 鋳造ホットインペラーおよびその製造方法
JPH10193087A (ja) * 1996-12-27 1998-07-28 Daido Steel Co Ltd ＴｉＡｌ製タービンローターの製造方法
JP2002235547A (ja) * 2001-02-09 2002-08-23 Shozo Shimizu ターボチャージャ用タービン軸の接合方法
WO2003021083A1 (fr) * 2001-09-03 2003-03-13 Mitsubishi Heavy Industries, Ltd Rotor hybride, son procede de fabrication et turbine a gaz

Family Cites Families (6)

* Cited by examiner, † Cited by third party
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JPS61215401A (ja) * 1985-03-20 1986-09-25 Yanmar Diesel Engine Co Ltd 過給機のタ−ビンホイ−ル
JPS62288302A (ja) * 1986-06-06 1987-12-15 Toyota Central Res & Dev Lab Inc 熱機関用回転体
JPH09100827A (ja) * 1995-10-06 1997-04-15 Hitachi Metals Ltd 疲労強度に優れる鋳造コンロッド
US6672838B1 (en) * 2000-07-27 2004-01-06 General Electric Company Method for making a metallic article with integral end band under compression
JP2004084550A (ja) * 2002-08-27 2004-03-18 Ishikawajima Harima Heavy Ind Co Ltd 翼植込み部の仕上加工方法
JP4127120B2 (ja) * 2003-05-28 2008-07-30 株式会社日立製作所 マイクロガスタービン発電装置およびそれに用いるトランジションピース

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5896101A (ja) * 1981-12-03 1983-06-08 Honda Motor Co Ltd タ−ビンホイ−ルの製造方法
JPH05212493A (ja) * 1992-02-06 1993-08-24 Mitsubishi Heavy Ind Ltd 精密鋳造翼の製造方法
JPH06229203A (ja) * 1993-02-01 1994-08-16 Daido Steel Co Ltd 鋳造ホットインペラーおよびその製造方法
JPH10193087A (ja) * 1996-12-27 1998-07-28 Daido Steel Co Ltd ＴｉＡｌ製タービンローターの製造方法
JP2002235547A (ja) * 2001-02-09 2002-08-23 Shozo Shimizu ターボチャージャ用タービン軸の接合方法
WO2003021083A1 (fr) * 2001-09-03 2003-03-13 Mitsubishi Heavy Industries, Ltd Rotor hybride, son procede de fabrication et turbine a gaz

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101596665B (zh) * 2008-06-03 2012-01-18 中国兵器工业集团第七○研究所 一种钛铝合金涡轮转轴三体结构连接的工艺方法
JP2013170487A (ja) * 2012-02-20 2013-09-02 Ihi Corp 過給機
CN104246167A (zh) * 2012-05-03 2014-12-24 博格华纳公司 减小应力的超级背板叶轮
KR20150004870A (ko) * 2012-05-03 2015-01-13 보르그워너 인코퍼레이티드 응력 감소 수퍼백 휠
KR101978381B1 (ko) * 2012-05-03 2019-05-14 보르그워너 인코퍼레이티드 응력 감소 수퍼백 휠
WO2018181085A1 (fr) * 2017-03-30 2018-10-04 三菱重工コンプレッサ株式会社 Procédé de fabrication de rotor, turbine et machine de rotation
JP2018168760A (ja) * 2017-03-30 2018-11-01 三菱重工コンプレッサ株式会社 インペラの製造方法、インペラ、及び、回転機械
US11143198B2 (en) 2017-03-30 2021-10-12 Mitsubishi Heavy Industries Compressor Corporation Impeller manufacturing method, impeller, and rotation machine

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