CN103422904A - Turbomachine having clearance control capability and system therefor - Google Patents

Turbomachine having clearance control capability and system therefor Download PDF

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Publication number
CN103422904A
CN103422904A CN2013101916260A CN201310191626A CN103422904A CN 103422904 A CN103422904 A CN 103422904A CN 2013101916260 A CN2013101916260 A CN 2013101916260A CN 201310191626 A CN201310191626 A CN 201310191626A CN 103422904 A CN103422904 A CN 103422904A
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CN
China
Prior art keywords
movable part
turbo machine
blade
turbine stage
machine according
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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
CN2013101916260A
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Chinese (zh)
Inventor
J.A.科特罗内奥
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General Electric Co
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General Electric Co
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Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of CN103422904A publication Critical patent/CN103422904A/en
Pending legal-status Critical Current

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    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A turbomachine having clearance control capability is provided and includes a turbine stage including a blade configured to rotate around a centerline, a movable portion of a casing circumferentially surrounding the turbine stage and a rotatable cam operably coupled to the movable portion and thereby configured to control an axial position of the movable portion. A radially outermost tip of the blade and an interior surface of the movable portion are sloped with respect to the centerline such that the controlled axial position of the movable portion is determinative of a clearance between the blade and the movable portion.

Description

There is the turbo machine of gap control ability and for its system
Technical field
Theme disclosed herein relates to turbo machine, and more particularly, relates to the turbo machine with gap control ability.
Background technique
Typical turbo machine such as gas turbine engine, steam turbine engines and compressor comprises compressor section, burner section and turbine.Compressor section compress inlet air and the air inlet of compression is transferred to the burner section.The air inlet of burner section burning compression and fuel are to produce high-energy fluid, and it is passed to turbine, and wherein, they expand in the power generating run.During these power generating runs, the continuous level of high-energy fluid and turbine blade is mutual aerodynamically, and the continuous level of this turbine blade is included in the turbine shell, wherein, between the end of shell and blade, gap is set.
At every one-level place, high-energy fluid impulse turbine blade, and bring out the rotation of turbine blade around rotor.Because high-energy fluid has high temperature and high pressure, so the frequent type based on ongoing turbine operation and through temperature distortion (that is, expand or shrink) of turbine blade and shell.This distortion can solve by according to worst case scenario, setting gap.Yet, under normal operating state, the gap of setting according to worst case scenario can be excessive, and can cause hydraulic performance decline due to the leakage between the end of shell and blade.
Summary of the invention
According to an aspect of the present invention, provide a kind of turbo machine with gap control ability, and this turbo machine comprises: turbine stage, it comprises the blade be configured to around the center line rotation; Circumferentially around the movable part of the shell of turbine stage; And rotatable cam, the axial position that it operationally is connected in movable part and is configured to thus control movable part.The radially outermost end of blade and the internal surface of movable part tilt about center line, make the controlled shaft of movable part to the gap between determining positions blade and movable part.
According to another aspect of the present invention, provide a kind of turbo machine with gap control ability, and this turbo machine comprises: turbine stage, it comprises the blade be configured to around the center line rotation; Shell, it is circumferentially around turbine stage and comprise front portion, rear portion and movable part, and movable part is axially planted and is fixed between front portion and rear portion, and limits the cam chair in its radially-outer surface; And rotatable cam, it is received in the cam chair of movable part and operationally is connected in it, and rotatable cam is configured to rotate to control according to it axial position of movable part thus.The radially outermost end of blade and the internal surface of movable part tilt about center line, make the controlled shaft of movable part to the gap between determining positions blade and movable part.
According to a further aspect of the invention, a kind of system that the gap control ability is provided to turbo machine is provided, and this system comprises: at least one or more turbine stage, and each at least one or more turbine stage comprises the blade be configured to around the center line rotation; Circumferentially around the movable part of the shell of one or more turbine stage at least; Rotatable cam, the axial position that it operationally is connected in movable part and is configured to thus control movable part; And controller.The radially outermost end of the blade of each at least one or more turbine stage and the internal surface of movable part tilt about center line, the controlled shaft that makes movable part in determining positions at least one or more turbine stage each blade and the gap between movable part.Controller operationally is connected in rotatable cam and is configured to thus control the operation of rotatable cam.
A kind of turbo machine with gap control ability, it comprises: turbine stage, it comprises the blade be configured to around the center line rotation; The movable part of shell, it is circumferentially around turbine stage; And rotatable cam, the axial position that it operationally is connected in movable part and is configured to thus control movable part, the radially outermost end of blade and the internal surface of movable part tilt about center line, make the controlled shaft of movable part to the gap between determining positions blade and movable part.
Preferably, blade is a plurality of, and a plurality of blade shroud is circumferentially arranged around center line.
Preferably, end and internal surface can be configured to roughly parallel to each other.
Preferably, rotatable cam comprises: live axle; And head, it is connected in live axle prejudicially.
Preferably, movable part comprises the radially-outer surface that limits cam chair, and cam chair receives rotatable cam.
Preferably, cam chair is configured to interfere rotatable cam, makes when rotatable cam during along the first or second contrary direction rotation, and movable part is respectively along the first or second contrary moving axially.
Preferably, cam chair comprises the circumferential wall surfaces of a pair of almost parallel.
Preferably, movable part comprises: central body; And flange, it extends in the forward and backward directions from central body respectively, flange respectively in the first and second recesses in being limited to front and rear vertically forward and direction backward move, front and rear is configured in respectively the place ahead and the rear of movable part.
Preferably, turbo machine also comprises the anti-rotational feature be configured on movable part.
Preferably, turbine stage comprises at least one or more turbine stage, each in turbine stage by movable part circumferentially around.
A kind of turbo machine with gap control ability, it comprises: turbine stage, it comprises the blade be configured to around the center line rotation; Shell, it is circumferentially around turbine stage and comprise front portion, rear portion and movable part, and movable part is axially planted and is fixed between front portion and rear portion, and limits the cam chair in its radially-outer surface; And rotatable cam, it is received in the cam chair of movable part and operationally is connected in it, rotatable cam is configured to rotate to control according to it axial position of movable part thus, the radially outermost end of blade and the internal surface of movable part tilt about center line, make the controlled shaft of movable part to the gap between determining positions blade and movable part.
Preferably, blade is a plurality of, and a plurality of blade shroud is circumferentially arranged around center line.
Preferably, end and internal surface can be configured to roughly parallel to each other.
Preferably, rotatable cam comprises: live axle; And head, it is connected in live axle prejudicially.
Cam chair is configured to interfere the head of rotatable cam, makes when rotatable cam around live axle during along the first or second contrary direction rotation, and movable part is respectively along the first or second contrary moving axially.
Preferably, cam chair comprises the circumferential wall surfaces of a pair of almost parallel.
Preferably, movable part comprises: central body; And flange, it extends in the forward and backward directions from central body respectively, flange respectively in the first and second recesses in being limited to front and rear vertically forward and direction backward move.
Preferably, turbo machine also comprises the anti-rotational feature be configured on movable part.
Preferably, turbine stage comprises at least one or more turbine stage, each in turbine stage by movable part circumferentially around.
A kind of system that the gap control ability is provided to turbo machine, it comprises: at least one or more turbine stage, each at least one or more turbine stage comprises the blade be configured to around the center line rotation; The movable part of shell, it is circumferentially around one or more turbine stage at least; Rotatable cam, the axial position that it operationally is connected in movable part and is configured to thus control movable part; And controller, the radially outermost end of the blade of each at least one or more turbine stage and the internal surface of movable part tilt about center line, the controlled shaft that makes movable part in determining positions at least one or more turbine stage each blade and the gap between movable part, and controller operationally is connected in rotatable cam and is configured to thus control the operation of rotatable cam.
The advantage of these and other and feature will become more apparent from the following description of carrying out by reference to the accompanying drawings.
The accompanying drawing explanation
Be considered to theme of the present invention is pointed out especially and clearly prescription in the claim of ending place of specification.From the following detailed description of carrying out by reference to the accompanying drawings, aforementioned feature and advantage with other of the present invention is apparent, in this accompanying drawing:
Fig. 1 is the side view according to the part of embodiment's turbo machine;
Fig. 2 is the rotatable cam of turbo machine part of Fig. 1 and the radial view of cam chair A-A along the line;
Fig. 3 is the side view according to the part of optional embodiment's turbo machine;
Fig. 4 is the radial view of the turbo machine part B-B along the line of Fig. 3; And
Fig. 5 is the side view according to the part of other embodiment's turbo machine.
Detailed description illustrates embodiments of the invention and advantage and feature with reference to accompanying drawing via example.
List of parts
10 turbo machines
20 turbine stage
21 blades
22 center lines
23 angled end
40 shells
41 annulars are anterior
410 towards back recesses
42 annular rear portions
420 recesses forward
43 annular movable parts
430 secondary recesses
44 annular center bodies
45 first annular flange flange
46 second annular flange flange
47 inclination inward faces
48 radially-outer surfaces
49 annular release tabs
60 rotatable cams
61 live axles
610 longitudinal axis
62 heads
80 controllers
90 cam chairs
91 recesses
92 wall surfaces
100 turbo machines
101 rotatable cams
102 elastic elements
103 live axles
104 anti-rotational features
105 torsion springs
200 first turbine stage
201 static blades are capable
202 rotation blades are capable
210 second turbine stage
211 static blades are capable
212 rotation blades are capable.
Embodiment
With reference to figure 1 and Fig. 2, the part of the turbo machine 10 with gap control ability is shown.As shown in Figure 1, this part of turbo machine 10 comprises turbine stage 20, shell 40, rotatable cam 60 and the controller 80 usually limited with static blade capable (that is, nozzle) and rotation blade capable (that is, movable vane).Turbine stage 20 can be configured in along in some turbine stage of each axial positions of turbo machine 10 at least one or more in any one, including but not limited to last turbine stage.Under any circumstance, turbine stage 20 comprises and is configured to the blade 21 in company with row of blades rotation around center line 22.In other words, blade 21 can be set to a plurality of blades of arranging with circumferential array 210 around center line 22.Each blade 21 has air foil shape, make blade 21 and the working fluid of the turbine stage 20 of flowing through between aerodynamics bring out alternately the rotation of blade 21 around center line 22.Each blade 21 also comprises its radially angled end 23 at outermost edge place.
When turbine stage 20 can be not covered, shell 40 is arranged to circumferentially around turbine stage 20, and, in some cases around extra level as shown in Figure 5, this is described below.Shell 40 comprises annular front portion 41, annular rear portion 42 and annular movable part 43.Annular movable part 43 is axially planted and is fixed between annular anterior 41 and annular rear portion 42, and comprises annular center body 44, the first annular flange flange 45, the second annular flange flange 46, inclination inward faces 47 and radially-outer surface 48.Annular anterior 41 forms and limits towards back recesses 410, and annular rear portion 42 forms similarly and limits recess 420 forward.
The first annular flange flange 45 from annular center body 44 vertically forward direction extend, and can be received in movably in back recesses 410.The second annular flange flange 46 from annular center body 44 vertically backward directions extend, and can be received in movably forward in recess 420.When annular movable part 43 axially moves forward, the first annular flange flange 45 penetrates in back recesses 410 relatively deeply, and the second annular flange flange 46 retreats but do not leave recess 420 forward from recess 420 forward.By contrast, when annular movable part 43 axially moves backward, the first annular flange flange 45 is from retreating towards back recesses 410 but not leaving towards back recesses 410, and the second annular flange flange 46 penetrates into forward in recess 420 relatively deeply.
Any that can be in for example the first annular flange flange 45 and the second annular flange flange 46 such as the anti-rotational feature of annular release tab 49 or both places are configured on movable part 43.These annular release tabs 49 can be received in the secondary recesses 430 be limited in annular anterior 41 and annular rear portion 42.As mentioned above, when annular movable part 43 axially moves forward or backward, annular release tab 49 penetrates in secondary recesses 430 and from it relatively deeply and retreats.When retreating, annular release tab 49 does not leave secondary recesses 430.
The distance that the inclination inward faces 47 of annular movable part 43 can limit at the controlled gap by between blade 21 and annular movable part 43 is configured in the radially outer of the angled end 23 of blade 21.Angled end 23 and inclination inward faces 47 can be arranged to roughly parallel to each other, and tilt with the distance decentre line 22 that backward directions D constantly increases vertically.Angled end 23 provides the improvement boundary layer conditions in turbine stage 20 downstreams, and allows relatively radical exhaust diffuser performance thus.
Rotatable cam 60 operationally is connected in annular movable part 43, and is configured to thus control the axial position of annular movable part 43.In the situation that angled end 23 and inclination inward faces 47 tilt about center line 22 is common, the controlled shaft of annular movable part 43 is to the controlled gap amount between angled end 23 and inclination inward faces 47 between determining positions blade 21 and annular movable part 43 or more specifically.This control to allow improves efficiency and the output of turbine stage 20 under covering state not, and also can be suitable for similarly and for covered turbine stage.
Rotatable cam 60 comprises live axle 61, and it can operationally be connected in the controller 80 be described in greater detail below, and head 62.Head 62 can be for example substantially circular, and can be connected to live axle 61 at the eccentric state second line of a couplet.When live axle 61 rotates around longitudinal axis 610, head 62 moves (bob) to and fro at the either side of live axle 61.
The radially-outer surface 48 of annular movable part 43 forms and limits cam chair 90.Cam chair 90 can receive the head 62 of rotatable cam 60, makes live axle 61 look and for example extends radially outwardly from annular movable part 43.Cam chair 90 is configured to mechanically interfere head 62, make when rotatable cam 60 around longitudinal axis 610 along first or during the second-phase opposite spin, annular movable part 43 is accordingly respectively along the first or second contrary moving axially.For this reason, according to embodiment, cam chair 90 can comprise the recess 91 be formed in radially-outer surface 48, and at front side and rear side, the circumferential wall surfaces 92 by a pair of almost parallel defines for it.
Head 62 closely is placed in recess 91, makes its sidewall each in abuts with wall surface 92 in opposite direction.When rotatable cam 60 rotates around longitudinal axis 610, the front side of head 62 and backside impingement wall surface 92, and therefore force the to-and-fro motion movably in the forward and backward directions of annular movable part 43.
Although head 62 and cam chair 90 are described as substantially circular element and the recess 91 defined by wall surface 92 in the above, will understand, this is only exemplary, and has other embodiment.For example, in the situation that head 62 is substantially circular, cam chair 90 also can be set to be limited to circle or the polygonal recess in radially-outer surface 48.
Controller 80 is set to for the member of the system of gap control ability is provided to turbo machine 10.Controller 80 operationally is connected in rotatable cam 60, and is configured to control the operation of rotatable cam 60.In other words, controller 80 can make rotatable cam 60 around longitudinal axis 610 rotations, make such as starting state, weaken under the various serviceability of state, instantaneous state and base load state, the controlled gap measurer between blade 21 and annular movable part 43 has various predetermined and/or suitable values.In addition, controller 80 also can be configured to sensing or measure in addition current gap value, and if these current gap values are excessive or reduce for current operation status, by correspondingly optionally operating rotatable cam 60, revises current gap value.
According to embodiment, feature described above can be set to single member or a plurality of member.Under latter event, a plurality of rotatable cams 60 all can operationally be connected in controller 80, and circumferentially configure around center line 22.Utilize this configuration, each rotatable cam 60 can be based on current state combination or operation dividually.
With reference to figure 3 and Fig. 4, and, according to optional embodiment, to turbo machine 100, provide the gap control ability.Turbo machine 100 comprises several in the above-mentioned feature that does not need again to describe in detail, such as turbine stage 20, blade 21 and movable part 43.In this case, rotatable cam 101 operationally is configured in the axially position of contiguous movable part 43, and is configured to by around live axle 103 rotations, impelling movable part 43 to overcome the biasing of elastic element 102.Elastic element 102 can be Compress Spring (wherein, elastic element 102 is configured in the side that movable part 43 is relative with rotatable cam 101), or is the extension spring of relative configuration.As shown in Figure 3, anti-rotational feature 104 is configurable on the radially-outer surface of movable part 43, and torsion spring 105 can be arranged on rotatable cam 101, so that movable part 43 is towards the gap biasing increased, with in the situation that control algorithm and the system failure are avoided friction.
With reference to figure 5, and according to other embodiment, shell 40 and especially movable part 43 can be configured to circumferentially around one or more turbine stage at least.For example, movable part 43 can be circumferentially around the first turbine stage 200 and the second turbine stage 210.As shown in Figure 5, the first turbine stage 200 and the second turbine stage 210 can be about sequentially configurations each other, and wherein, the second turbine stage 210 is positioned at the first turbine stage 200 downstreams.The first turbine stage 200 comprises capable (that is, nozzle) 201 of static blade and capable (that is, movable vane) 202 of rotation blade, and the second turbine stage 210 comprises capable (that is, nozzle) 211 of static blade and capable (that is, the movable vane) 212 of rotation blade.
Although in conjunction with the embodiment of limited quantity only, describe the present invention in detail, should easily understand, the present invention is not limited to these disclosed embodiments.On the contrary, the present invention can be changed into and is incorporated to up to now any amount of variation, change, replacement or the equivalent arrangements of not describing but matching with the spirit and scope of the present invention.In addition, although described various embodiment of the present invention, will understand, aspect of the present invention can only comprise some in the embodiment of description.Therefore, the present invention is not regarded as by aforesaid description restriction, but only by the scope restriction of claims.

Claims (10)

1. the turbo machine with gap control ability, it comprises:
Turbine stage, it comprises the blade be configured to around the center line rotation;
The movable part of shell, it is circumferentially around described turbine stage; And
Rotatable cam, the axial position that it operationally is connected in described movable part and is configured to thus control described movable part,
The radially outermost end of described blade and the internal surface of described movable part tilt about described center line, make the controlled shaft of described movable part to the gap between the described blade of determining positions and described movable part.
2. turbo machine according to claim 1, is characterized in that, described blade is a plurality of, and described a plurality of blade shroud is circumferentially arranged around described center line.
3. turbo machine according to claim 1, is characterized in that, described end and described internal surface can be configured to roughly parallel to each other.
4. turbo machine according to claim 1, is characterized in that, described rotatable cam comprises:
Live axle; And
Head, it is connected in described live axle prejudicially.
5. turbo machine according to claim 1, is characterized in that, described movable part comprises the radially-outer surface that limits cam chair, and described cam chair receives described rotatable cam.
6. turbo machine according to claim 5, it is characterized in that, described cam chair is configured to interfere described rotatable cam, makes when described rotatable cam during along the first or second contrary direction rotation, and described movable part is respectively along the first or second contrary moving axially.
7. turbo machine according to claim 5, is characterized in that, described cam chair comprises the circumferential wall surfaces of a pair of almost parallel.
8. turbo machine according to claim 1, is characterized in that, described movable part comprises:
Central body; And
Flange, it extends in the forward and backward directions from described central body respectively,
Described flange respectively in the first and second recesses in being limited to front and rear vertically forward and direction backward move, described front portion and described rear portion are configured in respectively the place ahead and the rear of described movable part.
9. turbo machine according to claim 1, is characterized in that, also comprises the anti-rotational feature be configured on described movable part.
10. turbo machine according to claim 1, is characterized in that, described turbine stage comprises at least one or more turbine stage, each in described turbine stage by described movable part circumferentially around.
CN2013101916260A 2012-05-22 2013-05-22 Turbomachine having clearance control capability and system therefor Pending CN103422904A (en)

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US13/477,839 US20130315716A1 (en) 2012-05-22 2012-05-22 Turbomachine having clearance control capability and system therefor
US13/477,839 2012-05-22

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CN103422904A true CN103422904A (en) 2013-12-04

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US (1) US20130315716A1 (en)
EP (1) EP2666971A1 (en)
JP (1) JP2013241932A (en)
CN (1) CN103422904A (en)
RU (1) RU2013123018A (en)

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EP2666971A1 (en) 2013-11-27

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Application publication date: 20131204