CN104153820A - Large meridional expansion variable-geometry turbine with stepped spherical end wall - Google Patents
Large meridional expansion variable-geometry turbine with stepped spherical end wall Download PDFInfo
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- CN104153820A CN104153820A CN201410349925.7A CN201410349925A CN104153820A CN 104153820 A CN104153820 A CN 104153820A CN 201410349925 A CN201410349925 A CN 201410349925A CN 104153820 A CN104153820 A CN 104153820A
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Abstract
The invention aims to provide a large meridional expansion variable-geometry turbine with a stepped spherical end wall. The large meridional expansion variable-geometry turbine comprises a case, a moving blade hub, a fixed blade hub and moving blades. The moving blade hub is arranged in the case. The moving blades are evenly distributed and fixed on the moving blade hub along the periphery of a hub. The fixed blade hub is arranged beside the moving blade hub. An adjustable fixed blade is arranged in front of each moving blade on the fixed blade hub. An upper rotating shaft is arranged on the upper end face of each adjustable fixed blade. A lower rotating shaft is disposed on the lower end face of each adjustable fixed blade. The outer side of every adjustable fixed blade is connected with the case through the upper rotating shaft arranged on the adjustable fixed blade. The fixed hub blade is provided with fixed blade grooves; the lower rotating shafts are all disposed in the fixed blade grooves. An adjusting rod is arranged on each upper rotating shaft and extends out of the case. The large meridional expansion variable-geometry turbine has the advantages complex flows at gap ends can be recombined, leak loss of the end gaps is reduced, the height of the end gaps can be kept unchanged when the fixed blades rotate, and variable condition characteristic is improved accordingly.
Description
Technical field
What the present invention relates to is a kind of turbine of gas turbine.
Background technique
Gas turbine often can be worked under off-design behaviour, and now turbine efficiency can significantly reduce.Variable geometry turbine technology can be improved gas turbine off-design efficiency effectively, and regulating the setting angle of Turbomachinery is a kind of effective change method of geometry.The variable stator vane angle structure of prior art, in order to ensure that Turbomachinery can rotate, the upper and lower end wall of stator blade will leave gap, thereby has caused the leakage loss of stator blade, has a strong impact on turbine efficiency; And for large meridian expansion variable geometry turbine, the large meridian angle of flare easily makes end wall Flow Structure Nearby slow down, and boundary layer thickens, and the ability of fluid opposing transverse-pressure gradient weakens, and then being easier to form Secondary Flow, these all can further increase variable geometry turbine petiolarea flow losses.In addition, when Turbomachinery rotates, petiolarea clearance height can change, especially more obvious in the pace of change of large meridian expansion variable geometry turbine intermediate gap height, has further affected the service behaviour of variable geometry turbine.
The adverse effect of leaking in order to reduce blade tip clearance, modern gas turbines mainly adopts initiatively and passive gap control.Passive clearance control method mainly adopts leaf top and casing processing, such as groove leaf top, the moulding of casing end wall etc., although this method can be improved turbine design point performance, cannot change and carry out effective Feedback clearance height.Initiatively clearance control method mainly heats or cooling casing or blade surface by gas compressor air-flow is drawn, make its corresponding expansion or contraction, thereby clearance height is changed and carries out feedback control, but there is the problem such as thermal inertia, structural configuration complexity in the method.The flow field problem bringing in order to solve large meridian expansionary channel, existing research is paid close attention in the optimization of meridional channel end wall molded line mostly.By the end of at present, for the existing unfavorable problem of large meridian expansion variable geometry turbine, prior art does not consider that mobile restructuring combines the control that blade tip clearance is leaked and to large meridian expansion petiolarea, does not more consider to improve the Study on Variable Condition Features of large meridian expansion variable geometry turbine.
Summary of the invention
The object of the present invention is to provide the gap petiolarea Complex Flows of can recombinating, reduce the loss of petiolarea clearance leakage, and then raising design point turbine efficiency, can keep again stator blade to rotate time, petiolarea clearance height is constant, thereby improves a kind of large meridian expansion variable geometry turbine with stepped ramp type sphere end wall of Study on Variable Condition Features.
The object of the present invention is achieved like this:
A kind of large meridian expansion variable geometry turbine with stepped ramp type sphere end wall of the present invention, comprise casing, movable vane wheel hub, moving vane, movable vane wheel hub is positioned in casing, between moving vane and moving vane, be evenly arranged and be fixed on movable vane wheel hub along circumference of hub direction, it is characterized in that: also comprise stator blade wheel hub, stator blade wheel hub is arranged on by movable vane wheel hub, along gas flow direction, in each moving vane front, adjustable stator blade is all set, adjustable stator blade is arranged on stator blade wheel hub, the upper-end surface of adjustable stator blade arranges running shaft, the lower end surface of adjustable stator blade arranges Shaft, the outside of each adjustable stator blade is all connected with casing by running shaft on it, stator blade film trap is set on stator blade wheel hub, Shaft is all arranged in stator blade film trap, the regulating lever that regulates adjustable stator blade angle is installed on upper running shaft, regulating lever extend out to outside casing.
The present invention can also comprise:
1, the axis of upper running shaft and Shaft is located along the same line, and the upper running shaft diameter of axle is greater than Shaft.
2, the hatching of casing inner side comprises the first import flat segments, first step molded line, the first sphere molded line, second step molded line, the second sphere molded line, the second outlet flat segments that are connected successively, wherein position, the corresponding adjustable stator blade upper-end surface of the first sphere molded line, the position of the corresponding moving vane of the second sphere molded line end, the section of the first sphere molded line and adjustable stator blade upper-end surface is circular arc type, and its concyclic heart.
3, the hatching in stator blade wheel hub outside comprises the second import flat segments, the 3rd step molded line, the 3rd sphere molded line that are connected successively, the hatching in movable vane wheel hub outside comprises the 4th sphere molded line, the second outlet flat segments that are connected successively, wherein position, the corresponding adjustable stator blade lower end surface of the 3rd sphere molded line, the position of the corresponding moving vane root of the 4th sphere molded line, the section of the 3rd sphere molded line and adjustable stator blade lower end surface is circular arc, and its concyclic heart.
4, the hatching in stator blade wheel hub outside comprises the second import flat segments being connected successively, the 3rd step molded line, the 3rd sphere molded line, the hatching in movable vane wheel hub outside comprises the 4th sphere molded line being connected successively, the second outlet flat segments, wherein position, the corresponding adjustable stator blade lower end surface of the 3rd sphere molded line, the position of the corresponding moving vane root of the 4th sphere molded line, the section of the 3rd sphere molded line and adjustable stator blade lower end surface is circular arc, and the first sphere molded line, the 3rd sphere molded line, the section of adjustable stator blade upper-end surface, the concyclic heart of section of adjustable stator blade lower end surface.
5, the first import flat segments and first step molded line angle are 30 °～75 °, axial distance between the left side end points of the first sphere molded line and adjustable stator blade leading edge leading edge top is that the axial distance between right side end points and the adjustable stator blade trailing edge top of the 5%～15%, first sphere molded line of the axial chord length in adjustable stator blade upper end portion is 5%～15% of the axial chord length in adjustable stator blade upper end portion, second step molded line and the first import flat segments angle are 30 °～75 °, axial distance between the left side end points of the second sphere molded line and moving vane leading edge top is 5%～20% of the axial chord length in moving vane upper end portion, the 3rd step molded line and the second import flat segments angle are 30 °～75 °, axial distance between the 3rd sphere molded line left-hand end point and adjustable stator blade leading edge root is 5%～15% of the axial chord length in adjustable stator blade underpart, axial distance between the 3rd sphere molded line right-hand end point and adjustable stator blade trailing edge root is 5%～15% of the axial chord length in adjustable stator blade underpart, between the upper-end surface of adjustable stator blade and the first sphere molded line, leave running clearance, between the lower end surface of adjustable stator blade and the 3rd sphere molded line, all leave running clearance.
Advantage of the present invention is: the flow control technique that the present invention is based on vorticla motion, by introduce suitable ledge structure on end wall, and then introducing separates whirlpool, together with Passage Vortex, the development of tip leakage vortex is played to certain inhibitory action, also large meridian expansion end wall construction is changed into ledge structure and the combination that is bordering on the sphere molded line that there is no expansion simultaneously, and then improved on the whole turbine clearance petiolarea mobile performance, thereby obviously improve the pneumatic efficiency of large meridian expansion variable geometry turbine; And, the upper and lower end face of adjustable stator blade is designed to concentric spherical structure by the present invention, and be total to the centre of sphere with the sphere section of casing and wheel hub, thereby while having ensured stator blade rotation, petiolarea clearance height is constant simultaneously, thereby has effectively improved the Study on Variable Condition Features of large meridian expansion variable geometry turbine.In addition, structure of the present invention is relatively simple, is also easy to engineering application.
Brief description of the drawings
Fig. 1 is meridian view of the present invention;
Fig. 2 a is the structural representation of casing part of the present invention, the structural representation that Fig. 2 b is hub portion of the present invention.
Embodiment
For example the present invention is described in more detail below in conjunction with accompanying drawing:
In conjunction with Fig. 1～2, the present invention is made up of wheel hub 1, adjustable stator blade 4, moving vane 5 and large meridian expansion end wall casing 8, adjustable stator blade 4 and moving vane 5 are along the circumferential direction evenly installed between wheel hub 1 and casing 8, adjustable stator blade 4 is front, moving vane 5 is rear, the upper-end surface 6 of adjustable stator blade and lower end surface 3 arrange respectively running shaft 7 and Shaft 2, its axle center on same spin axis so that variable stator vane angle rotate, and the diameter of axle of upper running shaft 7 is greater than Shaft 2, Shaft 2 only plays the role of positioning.Upper running shaft 7 is embedded in casing 8, and Shaft 2 is embedded in wheel hub 1, and moving vane 5 is arranged on wheel hub 1.Between casing 8 and blade upper-end surface 6 and wheel hub 1 and blade lower end surface 3, form respectively gap.
As shown in Fig. 2 (a), large meridian expansion end wall casing 8 successively by import flat segments, the stepped ramp type sphere section matching with adjustable stator blade top, the stepped ramp type tilting section matching with moving vane top and export flat segments and form.Import flat segments 9 and the stepped ramp type sphere section (11 matching with adjustable stator blade top, 13) connect in flex point 10, this stepped ramp type sphere section is made up of step molded line 11 and sphere molded line 13, wherein step molded line 11 is connected in flex point 12 with sphere molded line 13, and this stepped ramp type sphere section is connected in flex point 14 with the stepped ramp type sphere section matching with moving vane top, the stepped ramp type sphere section matching with moving vane top is made up of step molded line 15 and sphere molded line 17, wherein step molded line 15 is connected in flex point 16 with sphere molded line 17, finally this stepped ramp type sphere section is connected in flex point 18 with outlet flat segments 19.
As shown in Fig. 2 (b), wheel hub successively by import flat segments, the stepped ramp type sphere section matching with adjustable stator blade root, the tilting section being connected with moving vane root and outlet flat segments form.Import flat segments 23 is connected in flex point 24 with the stepped ramp type sphere section matching with adjustable stator blade root, this stepped ramp type sphere section is made up of step molded line 25 and sphere molded line 27, wherein step molded line 25 is connected in flex point 26 with sphere molded line 27, and this stepped ramp type sphere section connects in flex point 28 with the tilting section being connected with moving vane root, the tilting section being finally connected with moving vane root is connected in flex point 30 with outlet flat segments 31.
It should be noted that, the parameters that affects Optimum End wall construction form can obtain by means of existing computational fluid dynamics software numerical simulation or correlation test: for stepped ramp type sphere section part, step tilt angle is larger, step rear side separation whirlpool and the separation losses causing are larger, the inhibitory action of large separation vortex pair tip leakage vortex is also larger simultaneously, and then more effectively reduce petiolarea clearance leakage loss, therefore, have best step tilt angle for specific turbine generally, step inclined angle alpha 1, α 2, α 3 are 30 °～75 °.Consider turbine blade to be subject to the impact of three-dimensional non-steady flow field and deform, and consider blade material thermal expansion and vibration factor, the axial distance of stepped ramp type sphere section both sides flex point respectively and between adjustable stator blade leading edge 20, the corresponding radial position of trailing edge 21 should be large as far as possible, but consider the restriction of variable geometry turbine level axial length, this axial distance should be not excessive, this axial distance (w1, w2, w4 and w5) value is 5%～15% of the axial chord length of the corresponding radial position of adjustable stator blade; Similarly, for moving vane, deformable blade, vibration meeting that above factor is brought are larger, and the axial distance w3 between the radial position corresponding to moving vane leading edge 22 of step flex point is 5%～20% of the axial chord length of the corresponding radial position of moving vane.
In order further to reduce the loss of turbine blade petiolarea, the arc transition of carrying out appropriate size in the each flex point of end wall (10,12,14,16,18,24,26,28 and 30) is connected.
In addition, upper-end surface 6, the lower end surface 3 of adjustable stator blade 4 are designed to concentric spherical structure, and simultaneously and the sphere section centre of sphere altogether of casing 8 and wheel hub 1, and petiolarea clearance height remains unchanged when ensureing that stator blade rotates.
It should be noted that at the large meridian expansion variable geometry turbine with stepped ramp type sphere end wall of the present invention and also can combine other gap control measures such as active and passive with further control gap leakage flow.
A kind of large meridian expansion variable geometry turbine with stepped ramp type sphere end wall of the present invention, comprise large meridian expansion end wall casing, wheel hub, adjustable stator blade and moving vane are along the circumferential direction evenly installed between casing and wheel hub, adjustable stator blade is front, moving vane is rear, adjustable stator blade upper, lower end surface arranges respectively, Shaft, its axle center is on same spin axis, and diameter of axle difference, upper running shaft is embedded in casing, Shaft is embedded in wheel hub, moving vane is arranged on wheel hub, casing is successively by import flat segments, the stepped ramp type sphere section matching with adjustable stator blade top, the stepped ramp type tilting section matching with moving vane top and outlet flat segments composition, wheel hub is successively by import flat segments, the stepped ramp type sphere section matching with adjustable stator blade root, the tilting section being connected with moving vane root and outlet flat segments composition, adjustable stator blade upper, lower end surface is designed to concentric spherical structure, and be total to the centre of sphere with the sphere section of casing and wheel hub simultaneously.
The step tilt angle of the stepped ramp type sphere section that described casing matches with adjustable stator blade top is 30 °～75 °, axial distance between sphere section left side flex point and adjustable stator blade leading edge top be adjustable stator blade top axle to 5%～15% of chord length, the axial distance between sphere section right side flex point and adjustable stator blade trailing edge top is that adjustable stator blade top axle is to 5%～15% of chord length.
The step tilt angle of the stepped ramp type tilting section that described casing matches with moving vane top is 30 °～75 °, and axial distance between step flex point and moving vane leading edge top is that moving vane top axle is to 5%～20% of chord length.
The step tilt angle of the stepped ramp type sphere section that described wheel hub matches with adjustable stator blade root is 30 °～75 °, axial distance between sphere section left side flex point and adjustable stator blade leading edge root is 5%～15% of the axial chord length of adjustable stator blade root, and the axial distance between sphere section right side flex point and adjustable stator blade trailing edge root is 5%～15% of the axial chord length of adjustable stator blade root.
Between the upper-end surface and casing sphere of described large meridian expansion variable geometry turbine variable stator vane angle, all leave running clearance between lower end surface and wheel hub sphere.
Claims (8)
1. one kind has the large meridian expansion variable geometry turbine of stepped ramp type sphere end wall, comprise casing, movable vane wheel hub, moving vane, movable vane wheel hub is positioned in casing, between moving vane and moving vane, be evenly arranged and be fixed on movable vane wheel hub along circumference of hub direction, it is characterized in that: also comprise stator blade wheel hub, stator blade wheel hub is arranged on by movable vane wheel hub, along gas flow direction, in each moving vane front, adjustable stator blade is all set, adjustable stator blade is arranged on stator blade wheel hub, the upper-end surface of adjustable stator blade arranges running shaft, the lower end surface of adjustable stator blade arranges Shaft, the outside of each adjustable stator blade is all connected with casing by running shaft on it, stator blade film trap is set on stator blade wheel hub, Shaft is all arranged in stator blade film trap, the regulating lever that regulates adjustable stator blade angle is installed on upper running shaft, regulating lever extend out to outside casing.
2. a kind of large meridian expansion variable geometry turbine with stepped ramp type sphere end wall according to claim 1, is characterized in that: the axis of upper running shaft and Shaft is located along the same line, and the upper running shaft diameter of axle is greater than Shaft.
3. a kind of large meridian expansion variable geometry turbine with stepped ramp type sphere end wall according to claim 1 and 2, it is characterized in that: the hatching of casing inner side comprises the first import flat segments, first step molded line, the first sphere molded line, second step molded line, the second sphere molded line, the second outlet flat segments that are connected successively, wherein position, the corresponding adjustable stator blade upper-end surface of the first sphere molded line, the position of the corresponding moving vane of the second sphere molded line end, the section of the first sphere molded line and adjustable stator blade upper-end surface is circular arc type, and its concyclic heart.
4. a kind of large meridian expansion variable geometry turbine with stepped ramp type sphere end wall according to claim 1 and 2, it is characterized in that: the hatching in stator blade wheel hub outside comprises the second import flat segments being connected successively, the 3rd step molded line, the 3rd sphere molded line, the hatching in movable vane wheel hub outside comprises the 4th sphere molded line being connected successively, the second outlet flat segments, wherein position, the corresponding adjustable stator blade lower end surface of the 3rd sphere molded line, the position of the corresponding moving vane root of the 4th sphere molded line, the section of the 3rd sphere molded line and adjustable stator blade lower end surface is circular arc, and its concyclic heart.
5. a kind of large meridian expansion variable geometry turbine with stepped ramp type sphere end wall according to claim 3, it is characterized in that: the hatching in stator blade wheel hub outside comprises the second import flat segments being connected successively, the 3rd step molded line, the 3rd sphere molded line, the hatching in movable vane wheel hub outside comprises the 4th sphere molded line being connected successively, the second outlet flat segments, wherein position, the corresponding adjustable stator blade lower end surface of the 3rd sphere molded line, the position of the corresponding moving vane root of the 4th sphere molded line, the section of the 3rd sphere molded line and adjustable stator blade lower end surface is circular arc, and the first sphere molded line, the 3rd sphere molded line, the section of adjustable stator blade upper-end surface, the concyclic heart of section of adjustable stator blade lower end surface.
6. a kind of large meridian expansion variable geometry turbine with stepped ramp type sphere end wall according to claim 1 and 2, it is characterized in that: the first import flat segments and first step molded line angle are 30 °～75 °, axial distance between the left side end points of the first sphere molded line and adjustable stator blade leading edge leading edge top is that the axial distance between right side end points and the adjustable stator blade trailing edge top of the 5%～15%, first sphere molded line of the axial chord length in adjustable stator blade upper end portion is 5%～15% of the axial chord length in adjustable stator blade upper end portion, second step molded line and the first import flat segments angle are 30 °～75 °, axial distance between the left side end points of the second sphere molded line and moving vane leading edge top is 5%～20% of the axial chord length in moving vane upper end portion, the 3rd step molded line and the second import flat segments angle are 30 °～75 °, axial distance between the 3rd sphere molded line left-hand end point and adjustable stator blade leading edge root is 5%～15% of the axial chord length in adjustable stator blade underpart, axial distance between the 3rd sphere molded line right-hand end point and adjustable stator blade trailing edge root is 5%～15% of the axial chord length in adjustable stator blade underpart, between the upper-end surface of adjustable stator blade and the first sphere molded line, leave running clearance, between the lower end surface of adjustable stator blade and the 3rd sphere molded line, all leave running clearance.
7. a kind of large meridian expansion variable geometry turbine with stepped ramp type sphere end wall according to claim 4, it is characterized in that: the first import flat segments and first step molded line angle are 30 °～75 °, axial distance between the left side end points of the first sphere molded line and adjustable stator blade leading edge leading edge top is that the axial distance between right side end points and the adjustable stator blade trailing edge top of the 5%～15%, first sphere molded line of the axial chord length in adjustable stator blade upper end portion is 5%～15% of the axial chord length in adjustable stator blade upper end portion, second step molded line and the first import flat segments angle are 30 °～75 °, axial distance between the left side end points of the second sphere molded line and moving vane leading edge top is 5%～20% of the axial chord length in moving vane upper end portion, the 3rd step molded line and the second import flat segments angle are 30 °～75 °, axial distance between the 3rd sphere molded line left-hand end point and adjustable stator blade leading edge root is 5%～15% of the axial chord length in adjustable stator blade underpart, axial distance between the 3rd sphere molded line right-hand end point and adjustable stator blade trailing edge root is 5%～15% of the axial chord length in adjustable stator blade underpart, between the upper-end surface of adjustable stator blade and the first sphere molded line, leave running clearance, between the lower end surface of adjustable stator blade and the 3rd sphere molded line, all leave running clearance.
8. a kind of large meridian expansion variable geometry turbine with stepped ramp type sphere end wall according to claim 5, it is characterized in that: the first import flat segments and first step molded line angle are 30 °～75 °, axial distance between the left side end points of the first sphere molded line and adjustable stator blade leading edge leading edge top is that the axial distance between right side end points and the adjustable stator blade trailing edge top of the 5%～15%, first sphere molded line of the axial chord length in adjustable stator blade upper end portion is 5%～15% of the axial chord length in adjustable stator blade upper end portion, second step molded line and the first import flat segments angle are 30 °～75 °, axial distance between the left side end points of the second sphere molded line and moving vane leading edge top is 5%～20% of the axial chord length in moving vane upper end portion, the 3rd step molded line and the second import flat segments angle are 30 °～75 °, axial distance between the 3rd sphere molded line left-hand end point and adjustable stator blade leading edge root is 5%～15% of the axial chord length in adjustable stator blade underpart, axial distance between the 3rd sphere molded line right-hand end point and adjustable stator blade trailing edge root is 5%～15% of the axial chord length in adjustable stator blade underpart, between the upper-end surface of adjustable stator blade and the first sphere molded line, leave running clearance, between the lower end surface of adjustable stator blade and the 3rd sphere molded line, all leave running clearance.
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| CN108798788A (en) * | 2018-04-24 | 2018-11-13 | 哈尔滨工程大学 | A kind of big meridian expands aerodynamic arrangement's method of the orthogonal turbine of wide string and raising turbine performance |
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| CN114962342A (en) * | 2022-05-27 | 2022-08-30 | 哈尔滨工程大学 | Compressor tip area vibration structure |
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| CN105626158A (en) * | 2016-03-03 | 2016-06-01 | 哈尔滨工程大学 | Variable geometry turbine with vortex elimination hole structures in front of movable blades |
| CN105626159A (en) * | 2016-03-03 | 2016-06-01 | 哈尔滨工程大学 | Variable geometry turbine with wavy concaved structures on front edges of movable blades |
| CN106368973A (en) * | 2016-11-09 | 2017-02-01 | 哈尔滨工业大学 | Gap flow control method used between fixed blade and end wall of gas compressor and gas compressor |
| CN106368973B (en) * | 2016-11-09 | 2018-04-06 | 哈尔滨工业大学 | Gap flow control method and compressor between the stator blade and end wall of compressor |
| CN108571468A (en) * | 2018-03-08 | 2018-09-25 | 哈尔滨工程大学 | A kind of upper end wall construction for gas compressor moving blade clearance leakage of blade tip flow control |
| CN108798788A (en) * | 2018-04-24 | 2018-11-13 | 哈尔滨工程大学 | A kind of big meridian expands aerodynamic arrangement's method of the orthogonal turbine of wide string and raising turbine performance |
| CN114109522A (en) * | 2021-11-29 | 2022-03-01 | 清华大学 | Guide vane structure for controlling clearance loss and power system |
| CN114962342A (en) * | 2022-05-27 | 2022-08-30 | 哈尔滨工程大学 | Compressor tip area vibration structure |
| CN114962342B (en) * | 2022-05-27 | 2024-04-02 | 哈尔滨工程大学 | Compressor end region vibration structure |
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