CN104781509B - Wavy stator shield - Google Patents
Wavy stator shield Download PDFInfo
- Publication number
- CN104781509B CN104781509B CN201380059853.6A CN201380059853A CN104781509B CN 104781509 B CN104781509 B CN 104781509B CN 201380059853 A CN201380059853 A CN 201380059853A CN 104781509 B CN104781509 B CN 104781509B
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- Prior art keywords
- wavy
- fin
- compressor reducer
- stator shield
- shield
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- 239000000725 suspension Substances 0.000 claims abstract description 9
- 239000003638 chemical reducing agent Substances 0.000 claims description 37
- 238000005452 bending Methods 0.000 claims description 8
- 238000009434 installation Methods 0.000 claims description 6
- 239000007789 gas Substances 0.000 description 8
- 239000000567 combustion gas Substances 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000000354 decomposition reaction Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 229910003460 diamond Inorganic materials 0.000 description 1
- 239000010432 diamond Substances 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000005764 inhibitory process Effects 0.000 description 1
- 230000008450 motivation Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
Classifications
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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
- F01D9/00—Stators
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
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- 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
- F04D29/526—Details of the casing section radially opposing blade tips
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- 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
-
- 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
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
- F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Control Of Turbines (AREA)
Abstract
A kind of wavy stator shield has stator string suspension, the stator string suspension has the surface for changing to be formed multiple surface profiles in height, wherein, these profiles reduce the gap between adjacent fins during the performance positioning beyond scope of design of fin.
Description
Background technology
The disclosed embodiments are mainly related to gas-turbine unit.More specifically, present example is related to combustion gas whirlpool
The shield being used together with pivot fin (vane) in turbine.
In gas-turbine unit, conventional gas-turbine unit usually has front-end and back-end and front end with after
Inline (inline) is if its dry part between end.Air inlet or air intake duct are in the front end of engine.It is moved towards rear end,
It is the nozzle of compressor reducer, combustion chamber, turbine and the rear end in engine successively after air intake duct.Those skilled in the art
It becomes readily apparent that, can further include additional component within the engine, additional component is as being, for example, low pressure and high pressure compressor, height
Pressure and low-pressure turbine and external axis.However, this is not enumerating for exhaustive.Engine also usually has across starting
The inner shaft that the longitudinal axis shaft in center of machine is placed to ground.Inner shaft had not only been connected to turbine but also had been connected to air compressor, made
It obtains turbine and provides rotation input to air compressor to drive compressor blade.
In operation, air is compressed in compressor reducer and is mixed in the burner with fuel, for flowing with generating fair current
The burning gases of the dynamic heat by multiple turbine stages.These turbine stages extract energy from burning gases.Pressure turbine
The burning gases of heat being received from burner first and including stator nozzles component, which guides burning gases fair current
Ground passes through row's high pressure turbine rotor blade for being extended radially out from supporting rotor disk.In two-stage turbine machine, second
Grade stator nozzles component is located in the downstream of the first grade blade, the first grade blade again by from the second supporting rotor disk radially outwardly
One extended arranges the 2nd grade of rotor blade and follows.Burning gases can be converted into mechanical energy by turbine.
Fin or airfoil are generally designed to the main or optimum position for operating.However, depending on turbine
The expection operational situation of engine, fin can be actuated to alternative site.Current stator guard design utilizes circular cross section,
Fin is activated across the circular cross section.When fin is moved to the closed position beyond scope of design from open by design position
(off design closed position), the gap between fin and shield is due to the curvature of shield, the flowing road of fin
Diameter geometry and lower edge shape and increase, all these factors are that meet compressor reducer running requirements required.
When the gap increases, flow disruption can influence the desired use purpose of airfoil function and construction.Can enable
People it is desirable that, overcome these and other disadvantage so that for example reduced in the closure Angle Position beyond scope of design of fin
Gap between fin and shield.
Invention content
According at least some embodiments, a kind of gas turbine with arrival end, outlet end and multiple thruster parts is sent out
Wavy (contoured) stator shield fin elements in motivation include：Stator shield, it is substantially in circle which, which has,
The cross section of shape, the shield have front end, rear end and at least one table extended between the first end and the second end
There are multiple pivot parts, this multiple pivot part circumferentially to be placed around shield to support the trunnion of fin for face, the shield；With change
Change at least one surface of height, which is adjacent to the multiple pivot part and circumferentially extending.
According at least some embodiments, a kind of wavy stator shield includes：Front end, rear end and between front and rear end
At least one surface extended, at least one surface are tapered from front to back；Multiple regions with change in elevation, this
Multiple regions are placed around at least one surface, each in this multiple regions has wave crest and trough；Multiple pivots
Portion aperture, front interval of this multiple pivot part aperture around at least one surface are opened.
According to other embodiments, a kind of wavy stator shield includes：Front-end and back-end extend between front and rear end
At least one surface, there is fan-shaped string to suspend region on this at least one surface, and the sector region is circumferentially extending；It is multiple
Fin installation site, this multiple fin installation site are circumferentially placed between front and rear end.
Description of the drawings
The embodiment of the present invention is shown in following view.
Fig. 1 is the side cross-sectional, view of gas-turbine unit；
Fig. 2 is the decomposition perspective view of stator shield fin elements；
Fig. 3 is the perspective view of stator shield fin elements；
Fig. 4 is exemplary the side cross-sectional, view of stator shield fin elements；
Fig. 5 is the detailed perspective view of stator shield fin elements；
Fig. 6 is the rear view of the stator shield fin elements in first position；
Fig. 7 is the rear view of the stator shield fin elements in the second position；
Fig. 8 is the rear view of the stator shield fin elements in the third place；With
Fig. 9 is the curve graph with the relevant sail position in gap between shield and fin.
Specific implementation mode
It is described in detail referring now to the embodiment provided, one or more examples of these embodiments are in the accompanying drawings
It shows.Each example has been explanation the disclosed embodiments and unrestricted the disclosed embodiments and provides.In fact, this
Field technology personnel will be clear that, without departing substantially from the scope of the present disclosure or spirit, can make in the present example
Go out a variety of change and variations.For example, the feature of a part for being shown as or being described as one embodiment can be with another embodiment
It is used together in addition to generate further embodiment.Thus, it is therefore an objective to, the present invention cover drop into appended claims and it
Equivalent scheme in the range of this change and variation.
Referring to Fig.1-9, multiple embodiments of wavy stator shield can be used together with pivoting fin.Stator shield packet
Stator shield suspended surface is included, during engine operates, fin pivots in the stator shield suspended surface.The stator shield
Suspended surface has a varying height, and to eliminate the leakage between fin and shield, which usually pivots shield in fin
Occur when outer surface.Which reduce any flow disruptions or flow disturbance along fin or airfoil.
As used herein, term " axial " or longitudinal axis along engine " axially " is referred to
Dimension (dimension).It " forward " is referred to along towards engine with " axial " or " axially " term that is used together
Air intake duct is relatively more moved close to the direction of a component of engine inlets towards compared with another component.With
" axial " or the term " axially " being used together refer to edge towards engine nozzle or direction and another portion " backward "
Part is moved compared to relatively more close to the direction of a component of engine nozzle.
As used herein, it term " radial " or " radially " refers to longitudinal in the center of engine
The dimension extended between axis and outer circumference.The use of term " nearside " or " proximally " is individually or and term
" radial " or " radially " refers to the central longitudinal axis of edge direction or direction compared with another component relatively more together
Close to the direction movement of a component of center longitudinal axis.The use of term " distal side " or " distally " is individually or and term
" radial " or " radially " refer to together along towards outer circumference or towards compared with another component relatively more
For close to the movement of the direction of a component of outer circumference.
As used herein, term " lateral " or " laterally " refer to not only perpendicular to axial dimension but also
Perpendicular to the dimension of radial dimension.
Referring initially to Fig. 1, the side, sectional view of gas-turbine unit 10 is shown, the gas-turbine unit 10
With motor inlet end 12, wherein air, which enters, usually to be limited by compressor reducer 14, burner 16 and multistage pressure turbine 20
Propeller 13.Jointly, propeller 13 provides thrust or power during operation.Combustion gas turbine 10 can be used for aircraft industry,
Power generation, industry, shipping industry etc..According to purposes, it includes multistage compressor rather than fan that motor inlet end 12, which can be used as selection,.Combustion
Gas turbine 10 is axisymmetric about engine axis 26 or axis 24 so that multiple engine components surround the engine axis
26 or axis 24 rotate.In operation, air is entered by the air inlet end 12 of engine 10 and movement passes through at least one pressure
Contracting grade, there, air pressure increase and are directed to burner 16.Compressed air mixes combining combustion with fuel, to provide
The burning gases of the heat of burner 16 are left towards pressure turbine 20.At pressure turbine 20, carried from the burning gases of heat
Energy is taken, so as to cause the rotation of turbine blade, which leads to the rotation of axis 24 again.It wears the front of axis 24 towards engine
It crosses to continue the rotation of one or more compressor reducer grades 14, turbofan 18 or inlet fans blade according to turbine design.
Axisymmetric axis 24 extends to rear end from front end 12 across turbogenerator 10.Axis 24 extends along a length thereof
(journaled).Axis 24 can be hollow to allow low-pressure turbine arbor 28 therein with the independent side of rotation with axis 24
Formula rotates.The central axial line 26 that axis 24,28 can surround engine rotates.During operation, axis 24,28 is together with being connected to axis
, the other structures of such as rotor assembly of turbine 20 and compressor reducer 14 etc rotate together, so as to according to such as power generation, work
The using area of industry or aircraft industry etc generates power or thrust.
Referring still to Fig. 1, entrance 12 includes the turbofan 18 for having multiple blades.Turbofan 18 is connected by axis 28
Thrust to low-pressure turbine 19 and formation for turbogenerator 10.Low-pressure air can equally be used to aid in cooling engine
Component.
Referring now to Fig. 2, the decomposition perspective view of stator shield fin elements 30 is depicted.Multiple fins 40 surround shield 32
It is spaced apart, the major part in this multiple fin 40 does not show that.Show three fins 40 decomposited from the outer surface of shield.
However, for purposes of clarity, it should be appreciated that, it is placed with multiple fins 40 around shield 32.The shield of exemplary embodiment
Cover 32 is circular on cross section, and is conical butt (frusto-conical) in shape, has front end 34
With rear end 36.In the hollow center portion of shield, the thruster part 13 of gas-turbine unit 10 may pass through.It is exemplary
Shield 32 is located in 14 region of compressor reducer of engine.For example, multistage compressor generally include to be mounted on the rotor it is several
Arrange rotating vane and several row's stator vanes 40 between stator casing and shield 32.Shield is about engine 10
Axis 24 (Fig. 1) is axisymmetric.
Near front end 34 is multiple pivot parts 38, this multiple pivot part 38 is represented as in the exemplary embodiment
Multiple circular recess (pocket), wherein fin 40 is seated in this multiple circular recess for being rotated relative to shield 32.Shield
Larger diameter of the cover 32 also near from the small diameter near front end 34 to rear end 36 is tapered.Such as it will further read the public affairs
As being best understood from when opening, when fin 40 is seated in pivot part 38, fin 40 lower edge and shield 32 it is outer
Gap is formed between surface.In conventional shield, when fin is rotated to position beyond scope of design, circular cross section is in the wing
Lead to increased gap occur between piece and shield.However, present example provides a kind of wavy or variable surface height
It spends to reduce the gap in the position beyond scope of design of fin 40.
Fin 40 includes outside spindle 44 and internal mandrel 45.Mandrel 44,45 be formed as vertical line or with vertical angulation
Degree.For example, painted mandrel and vertically at the angle between 10 degree to 15 degree.At internally positioned mandrel 45 is button 42,
The button 42 is seated in together with mandrel 45 in inverted impulse body 38.Top button 56 also controls the engine passed through in outside spindle
Shell in rotation.
Referring now to Fig. 3, the perspective view of stator shield fin elements 30 is depicted.As previously mentioned, current cover assembly
30 are located in the compressor reducer 14 of turbogenerator.However, the principle embodied in wavy stator shield 32 can be used in
In the alternative site of engine, wherein utilize the stator vanes of shield and fin or airfoil, such as turbine.It is discribed
Stator shield 32 is in the inner radius of fin 40.Engine housing (not shown) can be used for providing to be pivoted for the outer diameter of fin 40
Position.Stator vanes cover assembly 30 utilizes the shield 32 with front end 34 and rear end 36.Shield 32 is substantially on cross section
Circle, as shown in the part in the view drawn.Diameter at front end 34 can be more than the diameter at rear end 36.Front end includes more
A pivot part 38, wherein can positioning tabs 40.Pivot part 38 can be recessed region, wherein fin or airfoil 40 position
It is pivoted at using button or guide portion 42.At the radial outward position of fin 40 is mandrel 44, which can be used for
The second end of fin 40 is installed to provide guided pivot or rotation.Mandrel 44 may pass through the aperture in engine housing with steady
Surely it lives mandrel and allows to be pivoted movement.Lever arm (not shown) is directed across the rotation of expected angular displacement, to provide use
In the different location of improvement efficiency and performance of the engine under multiple operational situations.Multiple fins 40 are attached in the front end of shield 34
The nearly circumference around shield 32 extends, although not showing that some fins 40 for purposes of clarity.
What is extended back from pivot part 38 is at least one shield surface 46, such as stator string suspended surface 46.Stator string
Larger diameter of the suspended surface 46 near from the small diameter near pivot part 38 to rear end 36 is tapered.The axial direction taper
(taper) change or in terms of height can be bending or can be straight line.
Other than the taper, stator string suspended surface 46 is wavy so that height along the circumferential direction changes.As utilized
Shown in circumferentially extending dotted line 48, empty curvature of a curve 48 depicts the profile of stator string suspended surface 46, circumferentially
Direction changes between lower height and high height.Not there is circular surface, dotted line are depicted as a result, along wavy or sinusoidal
The profile 48 on surface 46.According to one embodiment of the disclosure, stator string suspended surface 46 has wavy profile 48 so as in the wing
The mobile period of piece 40 reduces the gap between fin 40 and shield 32.According to alternate embodiment, in terms of height circumferentially
The variation in direction can be linear.In any embodiment, surface 48 includes multiple wave crests and trough.Wave crest or trough
Axis is roughly parallel to the axis 26 (Fig. 1) or angled with engine axis 26 of engine, and shield is from front end to rear
It holds tapered.It will such as be described further herein, profile 48 is significantly reduced by between fin 40 and shield 32
It interrupts in the flow field that gap is formed.When being moved between Angle Position of the fin in open Angle Position and closure, these gaps would generally
Negatively affect fin airfoil shape, the expection of function and construction uses purpose.
Illustrative fin or airfoil 40 include leading edge 50 and rear 52 and extend between leading edge 50 and rear 52
Apparent surface.Opposite surface define it will be appreciated that suction side and on the pressure side.In the radial direction of fin 40
Place is provided with external enlarged or button 56 outward.Mandrel or trunnion 44 may connect to lever arm or other feature with by the wing
Piece 40 is activated to desired location.The rotation of fin 40 provides the more than one optimum for fin or airfoil, with
The efficiency and performance of improvement are just provided under the different operational situations of gas-turbine unit 10.
In the lower end of fin 40, fin 40 is connected to button 42 by dummy slider (fillet) 54 at radial inner end.The wing
The lower edge 58 or fin suspension of piece 40 are bendings, and in the mobile period of fin 40, lower edge 58 moves far
From the conventional shield surface (Fig. 6) for being pure circle on cross section and being indicated with line 70.This is in lower flank edge 58 and string
Between suspended surface 46 gap is formed due to the separated geometry of the two elements.In the state of the art, it is
The increased gap that system generates reduces performance, air circulates and increases undesirable loss and inhibition in this region
The improvement of engine performance.Profile represented by wavy or bending dotted line 48 reduces between shield 32 and fin 40
Gap, to improve air turning beharvior and reduce the loss in the region.
Referring now to Fig. 4, the lateral cross-sectional view of the component 30 of Fig. 3 is depicted.Shield 32 is between front end 34 and rear end 36
It is shown by vertical section view, to depict the button 42 being seated in pivot part 38.Fin 40 further includes lower spindle or trunnion
45, the lower spindle or trunnion 45 extend downwardly into pivot part so that and fin 42 is pivotally secured in shield 32, and
And as previously mentioned, upper mandrel 44 is pivotably retained by engine housing.As equally shown in the accompanying drawings, stator string is outstanding
It is in axial direction bending that portion 46, which is set, between front end 34 and rear end 36, and is curved specifically in the rear portion of pivot part 38
Bent.According to alternate embodiment, surface 46 is in axial direction linearly tapered between front end 34 and rear end 36.
Referring now to Fig. 5, the detailed perspective view of shield 32 and fin 40 is depicted.Detail drawing is shown in vacant situation
And the pivot part 38 filled by fin 40.Button 42 is seated in the pivot part 38 of generally circular shape and fin 40 is logical
It crosses dummy slider 54 and is connected to button 42.Gap 60 is shown between the lower edge 58 and stator string suspension 46 of fin.Between being somebody's turn to do
The stator of gap due to the curvature between front end 34 and rear end 36 in axial direction and compared with the existing technology reduces.Equally, between being somebody's turn to do
Circumferencial direction arch of the gap by fin 40 along suspended surface 46 in the pivot part 38 moves that (arch moves (due to profile 48
It is caused) and be reduced.
Shown in Fig. 5, profile 48 is apparent due to the curvature of the dotted line 48 of the profile of expression stator shield 32
Ground is shown.Multiple axially extending contour lines 49 are equally illustrated in stator string suspended surface 46, this is multiple axially extending
Contour line 49 depicts another curvature of stator 32.It is combined with the lower edge 58 of fin 40, reduces fin 40 and stator
Gap between 32, this improve the engine performance of multiple positions by pivoting fin 40.Fortune relative to engine 10
Turn, when engine speed is zero or very close zero, fin 40 is closed.In the closed position, fin 40 is in profile
Near the maximum height on surface 48.Alternatively, when engine speed increases and when close to maximum value, fin 40 is close to profile table
The minimum altitude in face 48.
Referring now to Fig. 6-8, shield 32 is shown that fin 40 is shown as in multiple positions in the rearview looked forward
Set middle movement.With reference to the view, the best depiction profile of stator string suspended surface 46.Wavy or sinusoidal surface 48 is by first
The multiple protuberances at sector changed between height and the second height are formed.Although having used term sinusoidal, it should not be limited
The accurate sine curve being formed in mathematics aspect.On the contrary, the term in a general sense to indicate height in terms of repeatedly
Variation.Dotted line 70 is shown in this view to indicate the circular horizon shape of prior art institute shield.Line 70 can be also represented by fixed
Basic or the first height of fine silk strings used for the outer strings suspended surface 46.Alternatively, it is outstanding can be higher or lower than stator string for the line 70 of present example
The trough or lower height on surface are set, this is because surface 46 also in axial direction changes height as shown.The height of profile 48
Change and is shown by the difference between the first height 70 for quoting the profile and the second high height 72.Suspended surface 46 as a result,
Change height between the first height and the second height, and utilize the height of this variation, the gap between fin 40 is spread
The position painted in Fig. 6-8 is reduced.
In addition, being axial streamline 70 shown in attached drawing, the axial direction streamline 70 expression crosses stator shield 32 in fin 40
Between and along be parallel to engine axis 26 (Fig. 1) axial direction air stream direction.
Fin 40 can rotate between for example minus 3 degree and about 25 degree.Illustrative fin 40 can be along two rotation sides as a result,
To any of from middle position move about 14 degree.However, this is exemplary, and the angular range substituted can be set
It counts in fin movement.
Referring now to Fig. 7, fin is shown in middle position, more clearly depicts the lower edge of fin
Edge 58.According to foregoing exemplary range, fin 40 is in 11 degree of positions.This is typically middle position.Show in the figure 7
A pair of of gap arrow is gone out.Gap 60 depicts the gap that the profile 48 to be cooperated by the lower edge 58 with fin 40 provides.Together
When, show gap P, gap P is depicted at lower edge 58 and the prior art as being previously shown as line 70 is round
Larger gap between shield benchmark.By the embodiment, those skilled in the art can clearly see subtracting for the offer of profile 48
The difference lacked.
Referring now to Fig. 8, the second extreme position of fin 40 is depicted, at 25 degree of positions.Again, gap 60
It is more much smaller than with 70 relevant prior art gap P of shaped cover benchmark.
For those skilled in the art it is to be understood that according to the design feature of engine, fin can in a variety of shapes and shape
Formula.Therefore, the shape of profile can be formed the shape corresponding to fin lower edge by the arcuate motion of pre-selection.When right
When variable sail system optimizes, in the case of gap shrinks, to shield surface, mandrel angle, fin string suspension
Quantity and stroke be all designed/optimize, so as to reduce loss and improved performance.
Referring now to Fig. 9, shows and describe the angle of the fin measured as unit of spending (gap is in the wing with gap
Between piece lower edge 58 and shield string suspension 46) between relationship chart.As by 80 institute of line with diamond data points
Show, the gap between minus 10 degree of angle and 25 degree of angle increases fairly constantly.The prior art embodiment is determined
Sub- shield 32 is contour shape circular and without present example in shape.On the contrary, by square data points table
The line 82 shown starts from minus 3 degree of the advance position limited at range and be moved to 25 degree.Before increasing to 25 degree of positions, by line
82 gaps indicated degree are constants from about 0 degree to about 12.As a result, by comparing along 80,82 data point, this field
Technical staff will be recognized that the gap is more much smaller than in the stator shield of the prior art in wavy stator shield.
For purposes of illustration, the foregoing description for structures and methods is had been presented for.It is not intended to exhaustive
Or limit the invention to disclosed exact procedure and/or form, and obviously, according to the above instruction, many changes and
Variation is all possible.Feature described herein can be combined in any combination.The step of method described herein
Suddenly can be physically that possible any sequence executes.Institute it is realized that, wavy stator while there has been illustrated and described that
The particular form of shield, but it is not limited to this, and on the contrary, it will only be limited by investing this claim.
Claims (23)
1. the wavy stator shield fin elements in a kind of gas-turbine unit, the wavy stator shield fin elements
With arrival end, outlet end and multiple thruster parts, the wavy stator shield fin elements include：
Compressor reducer stator shield, the compressor reducer stator shield have generally circular cross section；
Fin, the fin are installed on the compressor reducer stator shield in its diameter inward position；
The compressor reducer stator shield has front end, rear end and at least one table extended between the front end and the rear end
Face；
The compressor reducer stator shield has multiple pivot parts, the multiple pivot part circumferential around the compressor reducer stator shield
It places to support the trunnion of fin on ground；
At least one surface with change in elevation, at least one surface with change in elevation are adjacent to described more
A pivot part is simultaneously circumferentially extending；
Wherein, at least one surface is wavy.
2. wavy stator shield fin elements according to claim 1, which is characterized in that described wavy for sinusoidal.
3. wavy stator shield fin elements according to claim 1, which is characterized in that at least one surface it is described
It places at the edge that surface with change in elevation is adjacent to the fin.
4. wavy stator shield fin elements according to claim 3, which is characterized in that described with change in elevation
Surface is the curvature of bending limited with the rotation close to the edge by the fin.
5. wavy stator shield fin elements according to claim 4, which is characterized in that the fin has suspension
Portion, the suspension and the surface with change in elevation inhibit leakage when the fin pivots.
6. wavy stator shield fin elements according to claim 1, which is characterized in that in the multiple pivot part
Each receive the button of multiple fins.
7. wavy stator shield fin elements according to claim 1, which is characterized in that described with change in elevation
The curvature axis on surface is roughly parallel to engine axis.
8. a kind of wavy compressor reducer stator shield, including：
Front end, rear end and at least one surface extended between the front end and the rear end；
At least one surface is tapered from the front end to the rear end；
Multiple regions with change in elevation, the multiple regions with change in elevation are put around at least one surface
It sets, each in the multiple regions with change in elevation is with wave crest and trough；
Multiple pivot part apertures, front interval of the multiple pivot part aperture around at least one surface are opened；
Wherein, at least one surface is wavy, and the compressor reducer stator shield is described in the diameter inward position installation of fin
Fin.
9. wavy compressor reducer stator shield according to claim 8, which is characterized in that described wavy for sinusoidal.
10. wavy compressor reducer stator shield according to claim 8, which is characterized in that described with change in elevation
Multiple regions are along the circumferential direction bendings from the first height to the second height.
11. wavy compressor reducer stator shield according to claim 8, which is characterized in that the multiple change in elevation edge
Circumferencial direction from the first height to the second height be linear.
12. wavy compressor reducer stator shield according to claim 8, which is characterized in that the compressor reducer stator shield
In axial direction change height.
13. wavy compressor reducer stator shield according to claim 12, which is characterized in that the height of the change is curved
Bent.
14. wavy compressor reducer stator shield according to claim 12, which is characterized in that the height of the change is straight
Linear.
15. wavy compressor reducer stator shield according to claim 8, which is characterized in that the wavy compressor reducer is fixed
Sub- shield further includes the fin for having lower-most edge.
16. wavy compressor reducer stator shield according to claim 15, which is characterized in that moved in the pivot of the fin
During dynamic, the lower-most edge engagement multiple regions with change in elevation.
17. wavy compressor reducer stator shield according to claim 8, which is characterized in that described with change in elevation
Multiple regions are the curvature of bending limited with the rotation close to the lower edge by fin.
18. a kind of wavy compressor reducer stator shield, including：
Front-end and back-end, at least one surface extended between the front end and the rear end；
There is fan-shaped string to suspend region at least one surface, and the sector string suspension region is circumferentially extending；
Multiple fin installation sites, the multiple fin installation site are circumferentially placed between the front end and the rear end,
The compressor reducer stator shield installs the fin in the diameter inward position of fin；
Wherein, at least one surface is wavy.
19. wavy compressor reducer stator shield according to claim 18, which is characterized in that described wavy for sinusoidal.
20. wavy compressor reducer stator shield according to claim 18, which is characterized in that the sector string suspends region
High height from lower height to the compressor reducer stator shield of the compressor reducer stator shield is bending.
21. wavy compressor reducer stator shield according to claim 18, which is characterized in that the wavy compressor reducer is fixed
Sub- shield further includes multiple fins, and the multiple fin is operatively connectable to the multiple fin installation site.
22. wavy compressor reducer stator shield according to claim 21, which is characterized in that every in the multiple fin
One all has the edge extended between leading edge and rear.
23. wavy compressor reducer stator shield according to claim 22, which is characterized in that the edge is in the fin
Pivot movement during engage fan-shaped string and suspend region.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US13/679093 | 2012-11-16 | ||
| US13/679,093 US20140140822A1 (en) | 2012-11-16 | 2012-11-16 | Contoured Stator Shroud |
| PCT/US2013/068421 WO2014078121A1 (en) | 2012-11-16 | 2013-11-05 | Contoured stator shrouds |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104781509A CN104781509A (en) | 2015-07-15 |
| CN104781509B true CN104781509B (en) | 2018-07-13 |
Family
ID=50002832
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380059853.6A Active CN104781509B (en) | 2012-11-16 | 2013-11-05 | Wavy stator shield |
Country Status (7)
| Country | Link |
|---|---|
| US (1) | US20140140822A1 (en) |
| EP (1) | EP2920430A1 (en) |
| JP (1) | JP2015537150A (en) |
| CN (1) | CN104781509B (en) |
| BR (1) | BR112015011191A2 (en) |
| CA (1) | CA2891070A1 (en) |
| WO (1) | WO2014078121A1 (en) |
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| WO2014163681A1 (en) * | 2013-03-10 | 2014-10-09 | Fulayter Roy D | Gas turbine engines and corresponding method |
| US9638212B2 (en) * | 2013-12-19 | 2017-05-02 | Pratt & Whitney Canada Corp. | Compressor variable vane assembly |
| US9533485B2 (en) * | 2014-03-28 | 2017-01-03 | Pratt & Whitney Canada Corp. | Compressor variable vane assembly |
| US9631504B2 (en) * | 2014-04-02 | 2017-04-25 | Solar Turbines Incorporated | Variable guide vane extended variable fillet |
| EP3009604B1 (en) * | 2014-09-19 | 2018-08-08 | United Technologies Corporation | Radially fastened fixed-variable vane system |
| US10287901B2 (en) | 2014-12-08 | 2019-05-14 | United Technologies Corporation | Vane assembly of a gas turbine engine |
| EP3051119A1 (en) * | 2015-01-30 | 2016-08-03 | ALSTOM Renewable Technologies | Turbine unit for hydraulic installation |
| EP3128132B1 (en) * | 2015-08-03 | 2019-03-27 | MTU Aero Engines GmbH | Turbo engine guide blade ring element |
| EP3176384B1 (en) | 2015-12-04 | 2023-07-12 | MTU Aero Engines AG | Inner shroud, corresponding inner shroud sector, vane assembly and turbomachine |
| EP3176385B1 (en) * | 2015-12-04 | 2022-01-26 | MTU Aero Engines AG | Guide- blade rim housing for a turbomachine and turbomachine with guide- blade rim housing |
| FR3048228B1 (en) * | 2016-02-25 | 2018-03-09 | Safran Aircraft Engines | PROPELLER HUB WITH VARIABLE SHAFT WITH RADIAL AND AXIAL DIMENSIONAL VARIATION |
| DE102016215784A1 (en) * | 2016-08-23 | 2018-03-01 | MTU Aero Engines AG | Positioning element with recesses for a guide vane assembly |
| US10815811B2 (en) | 2017-11-28 | 2020-10-27 | General Electric Company | Rotatable component for turbomachines, including a non-axisymmetric overhanging portion |
| DE102018203442A1 (en) | 2018-03-07 | 2019-09-12 | MTU Aero Engines AG | Inner ring for a turbomachine, vane ring with an inner ring, turbomachinery and method of making an inner ring |
| FR3100563B1 (en) * | 2019-09-06 | 2021-08-06 | Safran Aircraft Engines | Polyspherical turbomachine hub for variable pitch blades |
| DE102019216634A1 (en) * | 2019-10-29 | 2021-04-29 | MTU Aero Engines AG | GUIDE VANE ARRANGEMENT FOR A FLOW MACHINE |
| DE102019218911A1 (en) * | 2019-12-04 | 2021-06-10 | MTU Aero Engines AG | GUIDE VANE ARRANGEMENT FOR A FLOW MACHINE |
| US11359509B1 (en) * | 2020-11-23 | 2022-06-14 | Pratt & Whitney Canada Corp. | Variable guide vane assembly with bushing ring and biasing member |
| US11608747B2 (en) | 2021-01-07 | 2023-03-21 | General Electric Company | Split shroud for vibration reduction |
| US11572794B2 (en) | 2021-01-07 | 2023-02-07 | General Electric Company | Inner shroud damper for vibration reduction |
| US11965422B2 (en) * | 2022-08-02 | 2024-04-23 | Pratt & Whitney Canada Corp. | Variable guide vane assembly for gas turbine engine |
| US12078071B1 (en) | 2023-02-21 | 2024-09-03 | Rolls-Royce Corporation | Segmented compressor inner band for variable vanes in gas turbine engines |
| US11879480B1 (en) | 2023-04-07 | 2024-01-23 | Rolls-Royce North American Technologies Inc. | Sectioned compressor inner band for variable pitch vane assemblies in gas turbine engines |
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| DE1300194B (en) * | 1963-03-21 | 1969-07-31 | Costa Silar Dr Dipl Ing | Diffuser arrangement with adjustable blades for axial fans |
| DE2835349C2 (en) * | 1978-08-11 | 1979-12-20 | Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen | Adjustable grille for highly loaded compressors, especially of gas turbine engines |
| US4950129A (en) * | 1989-02-21 | 1990-08-21 | General Electric Company | Variable inlet guide vanes for an axial flow compressor |
| CA2056592A1 (en) * | 1990-12-21 | 1992-06-22 | Phillip D. Napoli | Multi-hole film cooled combustor liner with slotted film starter |
| GB9823840D0 (en) * | 1998-10-30 | 1998-12-23 | Rolls Royce Plc | Bladed ducting for turbomachinery |
| FR2814205B1 (en) * | 2000-09-18 | 2003-02-28 | Snecma Moteurs | IMPROVED FLOW VEIN TURBOMACHINE |
| ITTO20010445A1 (en) * | 2001-05-11 | 2002-11-11 | Fiatavio Spa | STATOR OF A VARIABLE GEOMETRY AXIAL TURBINE FOR AIRCRAFT APPLICATIONS. |
| DE10352787A1 (en) * | 2003-11-12 | 2005-06-23 | Mtu Aero Engines Gmbh | Guide vane grille and turbomachine with a vane grille |
| GB0504588D0 (en) * | 2005-03-05 | 2005-04-13 | Rolls Royce Plc | Pivot ring |
| FR2885182B1 (en) * | 2005-04-28 | 2010-11-26 | Snecma Moteurs | VARIABLE-TIMING STATOR VANE, PROCESS FOR REPAIRING A DAWN |
| DE102007027427A1 (en) * | 2007-06-14 | 2008-12-18 | Rolls-Royce Deutschland Ltd & Co Kg | Bucket cover tape with overhang |
| FR2933148B1 (en) * | 2008-06-25 | 2010-08-20 | Snecma | TURBOMACHINE COMPRESSOR |
| FR2941018B1 (en) * | 2009-01-09 | 2011-02-11 | Snecma | A VARIABLE CALIPER FOR A RECTIFIER STAGE, COMPRISING A NON-CIRCULAR INTERNAL PLATFORM |
| US8123471B2 (en) * | 2009-03-11 | 2012-02-28 | General Electric Company | Variable stator vane contoured button |
| EP2607625B1 (en) * | 2011-12-20 | 2021-09-08 | MTU Aero Engines AG | Turbomachine and stage of turbomachine |
| US9175567B2 (en) * | 2012-02-29 | 2015-11-03 | United Technologies Corporation | Low loss airfoil platform trailing edge |
-
2012
- 2012-11-16 US US13/679,093 patent/US20140140822A1/en not_active Abandoned
-
2013
- 2013-11-05 CN CN201380059853.6A patent/CN104781509B/en active Active
- 2013-11-05 CA CA2891070A patent/CA2891070A1/en not_active Abandoned
- 2013-11-05 WO PCT/US2013/068421 patent/WO2014078121A1/en active Application Filing
- 2013-11-05 BR BR112015011191A patent/BR112015011191A2/en not_active IP Right Cessation
- 2013-11-05 JP JP2015542683A patent/JP2015537150A/en active Pending
- 2013-11-05 EP EP13824424.9A patent/EP2920430A1/en not_active Withdrawn
Also Published As
| Publication number | Publication date |
|---|---|
| JP2015537150A (en) | 2015-12-24 |
| US20140140822A1 (en) | 2014-05-22 |
| BR112015011191A2 (en) | 2017-07-11 |
| CA2891070A1 (en) | 2014-05-22 |
| EP2920430A1 (en) | 2015-09-23 |
| WO2014078121A1 (en) | 2014-05-22 |
| CN104781509A (en) | 2015-07-15 |
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