CN101008402A - Method and apparatus for reducing axial compressor blade tip flow - Google Patents

Method and apparatus for reducing axial compressor blade tip flow Download PDF

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Publication number
CN101008402A
CN101008402A CNA2006101729989A CN200610172998A CN101008402A CN 101008402 A CN101008402 A CN 101008402A CN A2006101729989 A CNA2006101729989 A CN A2006101729989A CN 200610172998 A CN200610172998 A CN 200610172998A CN 101008402 A CN101008402 A CN 101008402A
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CN
China
Prior art keywords
passage
wing
blade
air
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
CNA2006101729989A
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Chinese (zh)
Inventor
董志锋
J·J·拉海姆
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General Electric Co
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General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of CN101008402A publication Critical patent/CN101008402A/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • 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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • 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
    • F05D2240/20—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

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

Abstract

A turbine machine (T1) of the type having a high pressure compressor positioned in a casing (C1) is provided with a plurality of rotating compressor blades (10-14) with at least one air channel (10C-14C) formed in the blades (10-14) for air flow communication from the base to the tip for extracting and pressurizing air from an inner area proximate the disk (20) and conveying the extracted and pressurized air into an area between the blade tip and casing (C1) for blocking air flow across the tips of the blades (10-14).

Description

Reduce the method and apparatus of axial compressor blade tip flow
Technical field and background of invention
The present invention relates to a kind of method and apparatus of tip stream of the Axial Flow Compressor that is used for reducing wing, described wing for example: blade and fin.Vane tip in the compressor zone of turbogenerator fails to be convened for lack of a quorum and causes the loss of compression efficiency and stall margin.In addition, the flow process recirculation along the Seal cage of the interior flow diameter between fin and the blade also can reduce compression performance.The method that a kind of solution reduces to flow at the tip in the prior art is the gap that reduces vane tip.Can utilize several different methods to realize aforesaid operations, comprise that the method for utilizing mechanics and/or calorifics controls housing and fin separating surface.These methods may cause most advanced and sophisticated friction, the loss of excessive wear and engine efficiency.
Summary of the invention
According to an aspect of of the present present invention, a kind of method of most advanced and sophisticated air-flow of the turbine airfoil that reduces to rotate in housing is provided, the tip of described turbine airfoil and housing with slight distance at interval, it is included in the step of radially extending passage that has the inlet of the substrate that is adjacent to wing and be arranged on the outlet on the tip of wing is set in the wing.Air is drawn out of from the zone that is close to the wing substrate and compresses, and is introduced in passage then and is transported to the wing tip by passage.Air is discharged from passage by the outlet that is positioned at the wing tip, and in the zone that enters under the pressure of abundance between wing tip and the housing, is used for resisting the axial flow of the suction side from the malleation side to wing.
According to a further aspect in the invention, a kind of method of most advanced and sophisticated air-flow of the turbine airfoil that reduces to rotate in housing is provided, the tip of described turbine airfoil and housing are with slight distance at interval, it comprises the following steps, promptly, setting has and is adjacent to being positioned at the inlet on the leading edge of a wing side and being positioned at first of outlet on the tip of wing and radially extending passage of wing substrate, and is provided with to have and is adjacent to being positioned at the inlet on the trailing edge side and being positioned at second of outlet on the tip of wing and radially extending passage of wing substrate.Air is drawn out of from the zone of contiguous wing substrate, and inlet passage, and is pumped to the wing tip via described passage.Air is by being positioned at the outlet discharge route at wing tip, and in the zone that enters under the pressure of abundance between wing tip and the housing, is used for resisting the axial flow of the suction side from the malleation side to wing.
According to another aspect of the present invention, a kind of turbomachine compressor wing is provided, comprise wing substrate, wing tip, and air-flow path, described air-flow path is the outlet that radially extends in the wing tip from the air inlet in the wing of contiguous wing substrate, be used to provide air seal, it can block the axial flow from the positive pressure side of wing to the negative pressure end of wing, thereby reduces the tip stream of compressor wing.
Description of drawings
In conjunction with following accompanying drawing, the present invention is carried out following description, wherein:
Fig. 1 is the part sectioned view of the Axial Flow Compressor part of the turbogenerator shown in one embodiment of the present of invention;
Fig. 2 be part compressor shown in Figure 1 local amplification profile;
Fig. 3 is the part sectioned view of the Axial Flow Compressor part of the turbogenerator shown in an alternative embodiment of the invention;
Fig. 4 is the local amplification profile of part compressor shown in Figure 3;
Fig. 5 is the part sectioned view of the Axial Flow Compressor part of the turbogenerator shown in the another embodiment of the present invention; And
Fig. 6 is the local amplification profile of part compressor shown in Figure 5.
Embodiment
Now, describe according to a kind of method and apparatus that is used for controlling axial compressor blade tip flow provided by the present invention in particular with reference to accompanying drawing, the component of the Axial Flow Compressor of described turbogenerator T1 part as shown in Figure 1.The stator vanes 15-19 that is positioned at the neutral position that turbogenerator " T1 " comprises compression blade 10-14 and is positioned at housing C1.Compression blade 10-14 comprises leading edge 10A-14A separately.
As shown in Figure 2, for the sake of clarity, shown blade 10 is at length amplified; And the mode of execution of blade 11-14 is identical with blade 10.Air is by coiling hole 10B in 20 and be drawn out of from the zone of the front edge side 10A of blade 10 and compressing.Hole 10B is communicated with path 10 C, and described path 10 C is via blade 10 and radially extends outwardly into the tip, and at described bit point, path 10 C passes by hole 10D.Notice that path 10 C can produce branch road before being drawn the tip of blade 10.The size of path 10 C and the position of branch road and quantity can be determined according to size, shape and the capacity of blade and the empirical value of engine performance, power, tip clearance and similar factor.Be noted that, in the accompanying drawings, in fact can't show tip clearance with the ratio of accompanying drawing, so tip clearance be completely little with respect to the ratio of accompanying drawing.
Now, with reference to Fig. 3, turbogenerator " T2 " comprises compression blade 30-34, and the stator vanes 35-39 that is positioned the neutral position in the housing C2.Compression blade 30-34 comprises trailing edge 30A-34A separately.
Among Fig. 4, for the sake of clarity, blade 31 is at length amplified, and the mode of execution of blade 30 and 32-34 is identical with blade 31.Air is drawn out of from the zone of the trailing edge side 31A of blade 31 by the hole 31B in the plate edge 40.Hole 31B is communicated with passage 31C, and described passage 31C is by blade 31 and radially extends outwardly into the tip, at described tip, preferably before being drawn through hole 31D, can form branch road.
With reference to Fig. 5, turbogenerator " T3 " comprises compression blade 50-54, and the stator vanes 55-59 that is positioned the neutral position in the housing C3.Compression blade 50-54 comprise separately leading edge 50A-54A and trailing edge 50B-54B separately.
What Fig. 6 showed is blade 52, and for the sake of clarity, described blade 52 is at length amplified, and blade 51 mode of executions are identical with 52-54.Air is by being positioned at the hole 52C and the 52D of plate edge 60, is drawn out of from the zone of the front edge side 52A of blade 52 and the zone of trailing edge side 52B.Hole 52C and 52D are communicated with respectively with passage 52E and 52F, and described passage 52E and 52F are by blade 52 and radially extend outwardly into the tip, at described bit point, preferably form branch road before being drawn through hole 52G.
In each above-mentioned embodiment, form aerodynamic sealing air-flow in the vane tip air discharged by the tip clearance between vane tip and housing zone and reduced or prevented blade tip flow.As mentioned above, the air of flow path extraction internally is transported to tip clearance, is used to form described air block.Because the air that is extracted is through the suction of compressor drum and when when bit point is discharged from blade, its pressure raises, thereby the resistance air-flow passes vane tip from the malleation side to suction side.
Said method can be used for low pressure compressor (booster) and high pressure compressor.When these methods of employing, there is not additional flow loss.In addition, the minimizing of air-flow is by aerodynamic air block, rather than realizes by the running clearance closely between vane tip and the housing, therefore can set and keep bigger fit up gap between vane tip and housing.So, when carrying out recirculation in the interior flow diameter between fin and blade, reduced the friction of vane tip.The air that extracts can be continuously internally flow path be drawn into vane tip, therefore, also can during power operation, provide continuous air block constantly for vane tip.
The method that the application describes also can be applicable in blisk (the integrated dish of blade), deflection or the hoop swallow-tail form blade.
Above-mentioned method and apparatus for the control axial compressor blade tip.
Multiple details of the present invention can change under the situation that does not break away from its scope.
In addition, description of aforesaid the preferred embodiments of the present invention and optimal mode only provide for the present invention is described, are not the purpose for restriction.Claims can limit the present invention.
    T1 Turbine
    T2 Turbine
    T3 Turbine
    C1 Housing
    C3 Housing
    10 Blade
    10A Leading edge
    10B Entrance
    10C Passage
    10D Outlet
    11 Blade
    11C Passage
    12 Blade
    12C Passage
    13 Blade
    13C Passage
    14 Blade
    14C Passage
    15 Fixed tab
    16 Fixed tab
    17 Fixed tab
    18 Fixed tab
    19 Fixed tab
    20 Dish
    31 Blade
    31A Trailing edge
    31B Entrance
    31C Passage
    31D Outlet
    50 Blade
    50A Leading edge
    50B Trailing edge
    50C Entrance
    50D Entrance
    50F Passage
    52 Blade
    52A Leading edge
    52B Trailing edge
    52C Entrance
    52D Entrance
    52E First passage
    52F Second channel
    52G Outlet

Claims (10)

1, a kind of turbo machine (T1), it is to have the high pressure compressor that is positioned at housing (C1), a plurality of rotation compression blades (10-14) of band vane tip separately, be fixed in each blade base on the spider (20), and the type that is positioned at a plurality of stator vanes (15-19) between separately the blade (10-14), comprise at least one air passageways (10C, 11C, 12C, 13C, 14C), it is formed in separately the blade (10-14), form airflow connection between being used for from the substrate to the tip, so that can extract and compress air from the inner region of adjacent discs (20), and with the air of described extraction and compression by passage (10C, 11C, 12C, 13C, 14C) be transported in the zone between vane tip and the housing (C1), be used for retardance from the most advanced and sophisticated air-flow of blade (10-14).
2, turbo machine as claimed in claim 1 (T1), wherein passage (10C) is drawn vane tip by a plurality of exit orifices (10D) respectively.
3, turbo machine as claimed in claim 1 (T1), wherein passage (10C) comprises the air inlet (10B) on the leading edge (10A) that is positioned at blade (10).
4, turbo machine as claimed in claim 1 (T2), wherein passage (31C) comprises the air inlet (31B) on the trailing edge (31A) that is positioned at blade (31).
5, turbo machine as claimed in claim 1 (T3), wherein passage (50F) comprises the air inlet (50C) on leading edge (50A) side that is positioned at blade (50) and is positioned at air inlet (50D) on trailing edge (50B) side.
6, turbo machine as claimed in claim 1 (T3), comprise first passage (52E) and second channel (52F), described first passage (52E) has the air inlet (52C) on leading edge (52A) side that is positioned at blade (52), and described second channel (52F) has the air inlet (52D) on trailing edge (52B) side that is positioned at blade (52).
7, turbo machine as claimed in claim 3 (T1), wherein passage (50F) comprises a plurality of exit orifices (52G) that are positioned at vane tip.
8, the method for the most advanced and sophisticated air-flow of a kind of minimizing turbine airfoil (10), described turbine airfoil is to rotate with housing (C1) slight distance compartment of terrain, and the step that comprises has:
(a) passage (10C) that radially extends that has the inlet (10B) of the substrate that is adjacent to wing and be positioned at the outlet (10D) at wing tip is set in wing (10);
(b) air in zone that will come from the substrate of contiguous wing (10) extracts and compresses in the passage (10C);
(c) by passage (10C) described air is transported to the wing tip; And
(d) outlet (10D) by being positioned at the wing tip under the pressure of abundance, is discharged to air in the zone between the most advanced and sophisticated and housing (C1) of wing, is used for blocking the tip that the axial flow air-flow passes wing (10).
9, leading edge (10A) side that the step of the passage (10C) that radially extends that method as claimed in claim 8, wherein said setting have the inlet (10B) of the substrate that is adjacent to wing (10) and be positioned at the outlet (10D) at wing tip is included in wing (10) forms the step of inlet (10B).
10, leading edge (31A) side that the step of the passage (31C) that radially extends that method as claimed in claim 8, wherein said setting have the inlet (31B) of the substrate that is adjacent to wing (31) and be positioned at the outlet (31D) at wing tip is included in blade (31) forms the step of inlet (31B).
CNA2006101729989A 2005-11-30 2006-11-30 Method and apparatus for reducing axial compressor blade tip flow Pending CN101008402A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US11/164636 2005-11-30
US11/164,636 US20070122280A1 (en) 2005-11-30 2005-11-30 Method and apparatus for reducing axial compressor blade tip flow

Publications (1)

Publication Number Publication Date
CN101008402A true CN101008402A (en) 2007-08-01

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US (1) US20070122280A1 (en)
EP (1) EP1793089A3 (en)
JP (1) JP2007154887A (en)
CN (1) CN101008402A (en)
CA (1) CA2569177A1 (en)

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CN101876324A (en) * 2009-04-30 2010-11-03 通用电气公司 Borescope plug with bristle
CN103670531A (en) * 2012-09-07 2014-03-26 罗伯特·博世有限公司 Blade wheel for continuous-flow machine and method for producing turbine wheel for continuous-flow machine
CN103925244A (en) * 2014-04-02 2014-07-16 清华大学 Large-flow high-load axial compressor for 300MW F-class heavy-duty gas turbine

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CN102628452B (en) * 2012-03-21 2014-07-16 朱晓义 Air compressor and automobile engine
JP6468532B2 (en) * 2015-04-27 2019-02-13 三菱日立パワーシステムズ株式会社 Compressor rotor, compressor, and gas turbine

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CN103670531A (en) * 2012-09-07 2014-03-26 罗伯特·博世有限公司 Blade wheel for continuous-flow machine and method for producing turbine wheel for continuous-flow machine
CN103925244A (en) * 2014-04-02 2014-07-16 清华大学 Large-flow high-load axial compressor for 300MW F-class heavy-duty gas turbine
CN103925244B (en) * 2014-04-02 2017-03-15 清华大学 A kind of big flow high load axial compressor and fan for 300MW F level heavy duty gas turbines

Also Published As

Publication number Publication date
EP1793089A2 (en) 2007-06-06
JP2007154887A (en) 2007-06-21
EP1793089A3 (en) 2007-10-24
US20070122280A1 (en) 2007-05-31
CA2569177A1 (en) 2007-05-30

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