JPH07279887A - Axial flow air compressor - Google Patents

Axial flow air compressor

Info

Publication number
JPH07279887A
JPH07279887A JP6076761A JP7676194A JPH07279887A JP H07279887 A JPH07279887 A JP H07279887A JP 6076761 A JP6076761 A JP 6076761A JP 7676194 A JP7676194 A JP 7676194A JP H07279887 A JPH07279887 A JP H07279887A
Authority
JP
Japan
Prior art keywords
blade
slit
air compressor
tip end
blade tip
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
JP6076761A
Other languages
Japanese (ja)
Inventor
Atsushi Shimizu
淳 清水
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.)
IHI Corp
Original Assignee
IHI Corp
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 IHI Corp filed Critical IHI Corp
Priority to JP6076761A priority Critical patent/JPH07279887A/en
Publication of JPH07279887A publication Critical patent/JPH07279887A/en
Pending legal-status Critical Current

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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • 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
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/125—Fluid guiding means, e.g. vanes related to the tip of a stator vane
    • 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade

Abstract

PURPOSE:To restrain break-away of the boundary layer at the rear side of a blade tip end so as to delay a stall in order to enlarge the stable operating range by providing a blade having a slit at its tip end composed of a leading end part and a trailing end part. CONSTITUTION:A slit 11 is formed in the tip end 5 of a rotor blade 3, and a slit 12 is formed in the tip end 6 of a stator vane 4. The slits 11, 12 are inclined in an air flowing direction. Accordingly, a part of air on the flank side 7 of the rotor blade 3 flows through the slit 11 thereof, and then flows around the rear side 8 of the rotor blade 3 as indicated by the arrows 13, 14. Similarly, a part of air on the flank side of the stator vane 4 flows through the slit 12 thereof and flows around the rear side of the stator vane 4. Accordingly, the break-away of the boundary layer is restrained on the rear side 8 of the tip end of the rotor blade 3, and the break-away of the boundary layer is also restrained on the rear side of the tip end 6 of the stator vane 4. Thereby it is possible to delay a stall so as to enlarge the stable operating range.

Description

【発明の詳細な説明】Detailed Description of the Invention

【０００１】[0001]

【産業上の利用分野】本発明は、ガスタービン用圧縮機
などの軸流空気圧縮機に関するものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an axial air compressor such as a compressor for a gas turbine.

【０００２】[0002]

【従来の技術】従来のガスタービン用軸流空気圧縮機
は、たとえば、図３に示すような構成からなっている。
図３において、１は回転軸、２はケーシング、３は動
翼、４は静翼、５は該動翼３の翼先端、６は該静翼４の
翼先端である。2. Description of the Related Art A conventional gas turbine axial flow air compressor has, for example, a structure as shown in FIG.
In FIG. 3, 1 is a rotating shaft, 2 is a casing, 3 is a moving blade, 4 is a stationary blade, 5 is a blade tip of the moving blade 3, and 6 is a blade tip of the stationary blade 4.

【０００３】図４は図３の切断線Ｂ−Ｂに沿う拡大断面
図である。図４において、７は該動翼３の腹側、８は同
じく背側、９は同じく入口端、１０は同じく出口端であ
る。すなわち、ガスタービンの燃焼用空気は動翼３の回
転により加圧され、静翼４で案内され、図示されていな
い燃焼室へ供給されるようになっている。FIG. 4 is an enlarged sectional view taken along section line BB of FIG. In FIG. 4, 7 is the ventral side of the moving blade 3, 8 is the back side, 9 is the inlet end, and 10 is the outlet end. That is, the combustion air of the gas turbine is pressurized by the rotation of the moving blades 3, guided by the stationary blades 4, and supplied to a combustion chamber (not shown).

【０００４】[0004]

【発明が解決しようとする課題】しかしながら、図３に
示した従来の軸流空気圧縮機においては、公知のよう
に、ある圧縮比とある回転速度および流速になると、動
翼３の翼先端５の背側８の中央部付近に境界層剥離によ
る失速が生じ、安定した作動ができなくなるという問題
点があった。However, in the conventional axial flow air compressor shown in FIG. 3, as is well known, when a certain compression ratio and a certain rotation speed and flow velocity are achieved, the blade tip 5 of the rotor blade 3 is formed. There was a problem that a stall occurred due to boundary layer separation in the vicinity of the central part of the back side 8 and stable operation was not possible.

【０００５】また静翼４についても、翼先端６の背側に
同様な失速が生じ、安定した作動ができなくなるとう問
題点があった。The stationary blade 4 also has a problem that a similar stall occurs on the back side of the blade tip 6 and stable operation cannot be performed.

【０００６】本発明は、このような問題点を解決しよう
とするものである。すなわち、本発明は、翼先端での失
速を抑制し、安定作動範囲を拡大することができる軸流
空気圧縮機を提供することを目的とするものである。The present invention is intended to solve such a problem. That is, it is an object of the present invention to provide an axial air compressor capable of suppressing stall at the blade tip and expanding the stable operation range.

【０００７】[0007]

【課題を解決するための手段】上記目的を達成するた
め、本発明の軸流圧縮機は、翼先端にスリットを有して
その翼先端が前側部分と後側部分とからなっている翼を
備えているものとした。In order to achieve the above object, an axial flow compressor according to the present invention has a blade having a slit at the blade tip and the blade tip having a front portion and a rear portion. I had it.

【０００８】[0008]

【作用】本発明によれば、翼先端にスリットを有してそ
の翼先端が前側部分と後側部分とからなっている翼を備
えているので、翼の腹側の空気の一部が前記スリットを
通って背側に至るため、翼先端背側での境界層剥離が抑
制され、失速を遅らせることができて、安定作動範囲が
拡大する。According to the present invention, since a blade having a slit at the blade tip and the blade tip having a front portion and a rear portion is provided, a part of the air on the ventral side of the blade is Since it reaches the back side through the slit, boundary layer separation on the back side of the blade tip is suppressed, stall can be delayed, and the stable operation range is expanded.

【０００９】[0009]

【実施例】図１は本発明の一実施例を示した側面断面図
であり、図２は図１の切断線Ａ−Ａに沿う断面図であ
る。図１において、符号１ないし６は図３の場合と同じ
であり、また図２において、符号７ないし１０は図４の
場合と同じである。1 is a side sectional view showing an embodiment of the present invention, and FIG. 2 is a sectional view taken along the section line A--A of FIG. 1, reference numerals 1 to 6 are the same as those in FIG. 3, and reference numerals 7 to 10 in FIG. 2 are the same as those in FIG.

【００１０】そして１１は前記動翼３の翼先端５の中央
に設けられたスリット、１２は前記静翼４の翼先端６の
中央に設けられたスリットである。すなわち、図１にみ
られる５１は該動翼３の翼先端前側部、５２は同じく後
側部、６１は該静翼４の翼先端前側部、６２は同じく後
側部である。Reference numeral 11 denotes a slit provided at the center of the blade tip 5 of the moving blade 3, and 12 denotes a slit provided at the center of the blade tip 6 of the stationary blade 4. That is, 51 shown in FIG. 1 is a blade tip front side portion of the moving blade 3, 52 is a rear side portion thereof, 61 is a blade tip front side portion of the stationary blade 4, and 62 is a rear side portion thereof.

【００１１】図１に示すように構成された軸流空気圧縮
機においては、動翼３の翼先端５にスリット１１を有
し、静翼４の翼先端６にスリット１２を有するので、動
翼３の腹側７の空気の一部がそのスリット１１を通って
背側８に至り、同様に、静翼４の腹側の空気の一部がそ
のスリット１２を通って静翼４の背側に至る。したがっ
て、動翼３の翼先端５の背側８での境界層剥離および静
翼４の翼先端６の背側での境界層剥離が抑制され、失速
を遅らせることができて、安定作動範囲が拡大する。In the axial air compressor constructed as shown in FIG. 1, since the blade tip 5 of the moving blade 3 has the slit 11 and the blade tip 6 of the stationary blade 4 has the slit 12, the moving blade A part of the air on the ventral side 7 of the No. 3 passes through the slit 11 to reach the back side 8, and similarly, a part of the air on the ventral side of the vane 4 passes through the slit 12 and the back side of the vane 4. Leading to. Therefore, the boundary layer separation on the back side 8 of the blade tip 5 of the moving blade 3 and the boundary layer separation on the back side of the blade tip 6 of the stationary blade 4 can be suppressed, and the stall can be delayed, and the stable operation range can be reduced. Expanding.

【００１２】しかも、図２の矢印１３と１４で示すよう
に、腹側７の空気の一部が背側８へ流れやすいようにす
るため、動翼３のスリット１１は空気の流れ方向に沿わ
しめて斜めに設けられている。また静翼４のスリット１
２についても、同様に斜めに設けられている。なお図１
の実施例では、動翼３にはスリット１１を、静翼４には
スリット１２を、つまり、両方の翼にスリットを設けて
いるが、空気圧縮機の使用条件によっては、スリットを
動翼３か静翼４のいずれか一方のみに設けただけでもよ
い場合もある。また翼が多段になっている場合は、スリ
ットを前段のみに、中段のみに、後段のみに設ける場合
もある。とくに、回転速度が大きい場合には、スリット
を後段の翼に設けたほうが効果的である。Moreover, as indicated by arrows 13 and 14 in FIG. 2, the slits 11 of the rotor blade 3 are arranged along the air flow direction so that a part of the air on the ventral side 7 can easily flow to the back side 8. It is installed diagonally. In addition, the slit 1 of the stationary blade 4
Similarly, 2 is also provided diagonally. Figure 1
In the embodiment, the moving blade 3 is provided with the slit 11 and the stationary blade 4 is provided with the slit 12, that is, both the blades are provided with slits. However, depending on the use condition of the air compressor, the slits may be provided to the moving blade 3 In some cases, only one of the stationary vanes 4 may be provided. When the blade has multiple stages, slits may be provided only in the front stage, only in the middle stage, and only in the rear stage. Especially, when the rotation speed is high, it is more effective to provide the slits on the blades at the subsequent stage.

【００１３】[0013]

【発明の効果】以上説明したように、本発明によれば、
翼先端にスリットを有してその翼先端が前側部分と後側
部分とからなっている翼を備えているので、翼の腹側の
空気の一部が前記スリットを通って背側に至るため、翼
先端背側での境界層剥離が抑制され、失速を遅らせるこ
とができて、安定作動範囲が拡大する効果がある。As described above, according to the present invention,
Since the wing tip has a slit and the wing tip has a wing consisting of a front part and a rear part, a part of the air on the ventral side of the wing reaches the back side through the slit. Boundary layer separation on the back side of the blade tip is suppressed, stall can be delayed, and the stable operation range is expanded.

【図面の簡単な説明】[Brief description of drawings]

【図１】本発明の一実施例を示した側面断面図である。FIG. 1 is a side sectional view showing an embodiment of the present invention.

【図２】図１の切断線Ａ−Ａに沿う断面図である。FIG. 2 is a cross-sectional view taken along the section line AA of FIG.

【図３】従来の技術の一例を示した側面断面図である。FIG. 3 is a side sectional view showing an example of a conventional technique.

【図４】図３の切断線Ｂ−Ｂに沿う断面図である。4 is a cross-sectional view taken along the section line BB in FIG.

【符号の説明】[Explanation of symbols]

３ 動翼 ４ 静翼 ５ 動翼の翼先端 ６ 静翼の翼先端 ７ 動翼の腹側 ８ 動翼の背側 １１ 動翼に設けられたスリット １２ 静翼に設けられたスリット ５１ 動翼の翼先端前側部 ５２ 動翼の翼先端後側部 ６１ 静翼の翼先端前側部 ６２ 静翼の翼先端後側部 3 rotor blade 4 stator blade 5 blade tip of rotor blade 6 blade tip of stator blade 7 ventral side of rotor blade 8 back side of rotor blade 11 slit provided in rotor blade 12 slit provided in stator blade 51 rotor blade Blade tip front side 52 Blade tip rear side of rotor blade 61 Blade tip front side of stator blade 62 Blade tip rear side of stator blade

Claims (5)

【特許請求の範囲】[Claims] 【請求項１】 翼先端にスリットを有してその翼先端が
前側部分と後側部分とからなっている翼を備えているこ
とを特徴とする、軸流空気圧縮機。1. An axial-flow air compressor, comprising a blade having a slit at the blade tip, the blade tip having a front portion and a rear portion. 【請求項２】 翼先端にスリットを有する翼が動翼であ
る請求項１記載の軸流空気圧縮機。2. The axial air compressor according to claim 1, wherein the blade having a slit at the blade tip is a moving blade. 【請求項３】 翼先端にスリットを有する翼が静翼であ
る請求項１記載の軸流空気圧縮機。3. The axial air compressor according to claim 1, wherein the blade having a slit at the blade tip is a stationary blade. 【請求項４】 スリットが空気の流れ方向に沿って腹側
から背側へと斜めに設けられている請求項１、２または
３記載の軸流空気圧縮機。4. The axial air compressor according to claim 1, 2 or 3, wherein the slits are provided obliquely from the ventral side to the dorsal side along the air flow direction. 【請求項５】 スリットが翼先端の中央に位置している
請求項１、２、３または４記載の軸流空気圧縮機。5. The axial flow air compressor according to claim 1, wherein the slit is located at the center of the blade tip.
JP6076761A 1994-04-15 1994-04-15 Axial flow air compressor Pending JPH07279887A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP6076761A JPH07279887A (en) 1994-04-15 1994-04-15 Axial flow air compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP6076761A JPH07279887A (en) 1994-04-15 1994-04-15 Axial flow air compressor

Publications (1)

Publication Number Publication Date
JPH07279887A true JPH07279887A (en) 1995-10-27

Family

ID=13614585

Family Applications (1)

Application Number Title Priority Date Filing Date
JP6076761A Pending JPH07279887A (en) 1994-04-15 1994-04-15 Axial flow air compressor

Country Status (1)

Country Link
JP (1) JPH07279887A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103953579A (en) * 2014-04-24 2014-07-30 中国科学院工程热物理研究所 Gas compressor rotor blade with top slit and design method
WO2015072256A1 (en) * 2013-11-15 2015-05-21 株式会社Ihi Vane structure for axial flow turbomachine and gas turbine engine
EP3255244A1 (en) * 2016-05-20 2017-12-13 United Technologies Corporation Tandem tip blades and corresponding gas turbine engine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015072256A1 (en) * 2013-11-15 2015-05-21 株式会社Ihi Vane structure for axial flow turbomachine and gas turbine engine
JPWO2015072256A1 (en) * 2013-11-15 2017-03-16 株式会社Ihi Axial turbomachine blade structure and gas turbine engine
CN103953579A (en) * 2014-04-24 2014-07-30 中国科学院工程热物理研究所 Gas compressor rotor blade with top slit and design method
EP3255244A1 (en) * 2016-05-20 2017-12-13 United Technologies Corporation Tandem tip blades and corresponding gas turbine engine
US10151322B2 (en) 2016-05-20 2018-12-11 United Technologies Corporation Tandem tip blade

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