CN203584475U - Turbine runner sealing structure and aeroengine turbine structure - Google Patents
Turbine runner sealing structure and aeroengine turbine structure Download PDFInfo
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- CN203584475U CN203584475U CN201320812074.6U CN201320812074U CN203584475U CN 203584475 U CN203584475 U CN 203584475U CN 201320812074 U CN201320812074 U CN 201320812074U CN 203584475 U CN203584475 U CN 203584475U
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Abstract
The utility model discloses a turbine runner sealing structure and an aeroengine turbine structure, relates to the technical field of aeroengines and solves the technical problem in the prior art that the sealing effect of a shroud is poorer because leaked flow is very serious at the radial clearances of the surfaces, far away from the rotation axis of a turbine, of a case and the shroud. The turbine runner sealing structure comprises a sealing platform, wherein the sealing platform is fixedly arranged on the outer cap of a guider in a turbine runner; in the radial direction of the turbine runner, intersecting parts and a gap exist between the shroud edges of shrouded blades in the sealing platform and the turbine runner. The aeroengine turbine structure comprises the case, the guider, the shrouded blades and the turbine runner sealing structure. The turbine runner sealing structure is used for improving the sealing effect of the turbine runner so as to improve the efficiency of the turbine.
Description
Technical field
The utility model relates to aero engine technology field, relates in particular to a kind of turbine runner seal structure and the aero-turbine structure of this turbine runner seal structure is set.
Background technique
The Real Flow Field of turbomachine inside is very complicated, spatially shows as mobile three dimensional type, shows as in time mobile non-stationarity.Add fluid viscosity and compressible impact, vane machine is inner to be existed complex vortex such as horseshoe vortex, Passage Vortex, whirlpool, angle and whirlpool, gap, and shock wave and the mutual interference of boundary layer phase, and dynamic and static leaf such as interferes mutually at the various Complex Phenomena in Vertical Bell Jars.
Between turbine rotor blade blade tip and casing, there is larger blade tip clearance, there is the leading pressure reduction of circumferential and axial in rotor blade Ye Ding region, circumferentially pressure reduction causes that the high-pressure gas of pressure side flows to suction surface by blade tip clearance, form blade tip clearance leakage flow, leakage flow and the effect of blade grid passage main flow form reveals whirlpool.Leakage flow has reduced the load of blade, and useful work is not done in the combustion gas of leakage substantially, reveals whirlpool and produces and dissipate and change the leaf grating angle of giving vent to anger, and meanwhile, leakage flow and leakage vortex drag plug mainstream channel, these aspects have all increased the aerodynamic loss of turbine.In addition, leakage flow and leakage whirlpool have also increased near the cooling difficulty of conducting heat of turbine blade-tip, and affect largely the non-stationarity in flow field, downstream.
Radial clearance between turbine casing and rotor blade blade tip has a significant impact turbine efficiency, and it is very large on engine performance impact.Research shows, an advanced twin-stage turbogenerator, if its radial clearance increases 1mm, turbine efficiency reduces approximately 2.5%, directly causes engine oil consumption rate to increase approximately 2.6%.Therefore, should reduce radial clearance, but too little rotor and the casing of can causing again in gap scratches as far as possible.
The leakage that radial clearance causes has circumferential gas leakage and axially gas leakage substantially.
For reducing the circumferential leakage causing due to radial clearance, turbine rotor blade that aspect ratio is larger is many, and at blade tip band integral shroud, integral shroud has reduced vane tip and by leaf basin, has been flowed to the circumferential leakage flow of blade back, thereby reduced, reveals loss, improves turbine efficiency.Shrouded blade (shrouded blade is comprised of integral shroud, blade, middle blade root and tenon) can effectively reduce leaf top leakage flow.
Shrouded blade has reduced the leaf top leakage loss that circumferential pressure reduction causes, but it still exists the gap between integral shroud top surface and casing, and the axial pressure difference in rotor blade Ye Ding region still can promote to reveal and flow.Leakage flow flows into leaf top cavity volume from the axial clearance between guider (guider is comprised of guider inside and outside ring and guide vane) outer shroud trailing edge and the rotor integral shroud leading edge of certain turbine stage, the integral shroud sealing teeth of flowing through, from the axial clearance between this grade of rotor integral shroud trailing edge next stage guider, import main flow, produce entropy increasing and cause aerodynamic loss, directly reduce the power stage of turbine stage.
In turbine design, pneumatic conceptual design goes out continuous hot meridional channel, and structure discipline, through work such as cold and hot conversion, cell cube division, spare part designs, obtains typically turbine structure as shown in Figure 1.As can be seen from Figure 1, the continuity of runner is not guaranteed, in turbo driving process, and the upstream step of rotor blade integral shroud leading edge forming surface, this has just destroyed the streamlined characteristic of fluid.Leakage flow, under the driving of rotor leaf top axial pressure difference, flows into main flow from integral shroud trailing edge, and therefore main flow occurs to separate and generation aerodynamic loss.
Therefore at least there is following technical problem in prior art:
Prior art exist casing and integral shroud more serious away from the radial surface gap location leakage flow of turbine rotary axis, cause the integral shroud poor technical problem of effect of obturaging.
Model utility content
One of them object of the present utility model is the aero-turbine structure that proposes a kind of turbine runner seal structure and this turbine runner seal structure is set.Solved prior art exist casing and integral shroud more serious away from the radial surface gap location leakage flow of turbine rotary axis, cause the integral shroud poor technical problem of effect of obturaging.Many technique effects that the utility model optimal technical scheme can produce refer to below sets forth.
For achieving the above object, the utility model provides following technological scheme:
The turbine runner seal structure that the utility model provides, comprises the platform of obturaging, wherein:
The guider that the described platform of obturaging is fixedly installed in turbine runner is labeled outward;
There is alternating share between the two and have gap between the two in obturage at turbine in the radial direction, the integral shroud edge of the shrouded blade in platform and described turbine runner.
At one, preferably or alternatively in embodiment, described turbine runner seal structure also comprises double wedge, wherein:
The platform of obturaging described in described double wedge is fixedly installed on approaches the surface of described turbine rotary axis or is fixedly installed on the integral shroud edge of described shrouded blade away from the surface of described turbine rotary axis, described double wedge position between the described platform of obturaging approach the surface of described turbine rotary axis and the integral shroud edge of described shrouded blade away from the gap between the surface of described turbine rotary axis in; Or,
The platform of obturaging described in described double wedge is fixedly installed on approaches the surface of described turbine rotary axis away from the surface of described turbine rotary axis or the integral shroud edge that is fixedly installed on described shrouded blade, described double wedge position is between the described platform of obturaging approaches the gap between the surface of described turbine rotary axis away from the surface of described turbine rotary axis and the integral shroud edge of described shrouded blade in.
At one preferably or alternatively in embodiment, the described platform of obturaging is fixedly installed on the end of the mounting edge of the outer nearly described turbine rotary axis of crown grafting of described guider, described in described double wedge is fixedly installed on, obturage on platform, and described double wedge extends away from the surperficial direction of described turbine rotary axis towards the integral shroud edge that approaches described shrouded blade.
At one, preferably or alternatively in embodiment, the outer profile size of described double wedge dwindles away from the surperficial direction of described turbine rotary axis gradually towards the integral shroud edge that approaches described shrouded blade.
At one, preferably or alternatively in embodiment, the end of the mounting edge of the outer nearly described turbine rotary axis of crown grafting of described guider approaches between the region of described turbine rotary axis and the integral shroud edge of described shrouded blade and have gap on the axial direction of described turbine.
At one, preferably or alternatively in embodiment, described guider comprises the first guider and the second guider, described in the platform of obturaging comprise first platform and second platform of obturaging of obturaging, wherein:
Described double wedge comprises and is fixedly installed on described first obturage the first double wedge on platform and be fixedly installed on described second the second double wedge of obturaging on platform;
Described first platform of obturaging is arranged on described the first guider and is preced with trailing edge outward and approaches the end of the mounting edge of described turbine rotary axis, and described the first double wedge extends away from the surperficial direction of described turbine rotary axis towards the integral shroud leading edge that approaches described shrouded blade;
Described second platform of obturaging is arranged on described the second guider and is preced with leading edge outward and approaches the end of the mounting edge of described turbine rotary axis, and described the second double wedge extends away from the surperficial direction of described turbine rotary axis towards the integral shroud trailing edge that approaches described shrouded blade.
At one preferably or alternatively in embodiment, the gap that described the second guider is preced with outward between the integral shroud trailing edge of leading edge and described shrouded blade forms guide channel.
At one preferably or alternatively in embodiment, described the second guider is preced with that end that leading edge approaches the mounting edge of described turbine rotary axis approaches gap between the region of described turbine rotary axis and the integral shroud trailing edge of described shrouded blade and the integral shroud trailing edge of described the second double wedge and described shrouded blade is connected and forms guide channel away from the gap between the surface of described turbine rotary axis outward.
At one preferably or alternatively in embodiment, described the second guider is preced with the region division that end that leading edge approaches the mounting edge of described turbine rotary axis approaches described turbine rotary axis outward the first water conservancy diversion groove, the integral shroud trailing edge of described shrouded blade is provided with the second water conservancy diversion groove, and what described the first water conservancy diversion groove and described the second water conservancy diversion groove were all positioned at described guide channel goes out head piece place.
At one preferably or alternatively in embodiment, the integral shroud leading edge of described shrouded blade approach spacing between surface and the described turbine rotary axis of described turbine rotary axis be not less than described the first guider be preced with outward surface that mounting edge that trailing edge approaches described turbine rotary axis approaches described turbine rotary axis at the upper end wall inviscid flow of described turbine runner to the elongated surfaces in direction and the spacing between described turbine rotary axis.
At one preferably or alternatively in embodiment, described the first guider is preced with that end that trailing edge approaches the mounting edge of described turbine rotary axis approaches gap between the region of described turbine rotary axis and the integral shroud leading edge of described shrouded blade and the integral shroud leading edge of described the first double wedge and described shrouded blade is connected and forms channel of resistance to flow away from the gap between the surface of described turbine rotary axis outward; Described channel of resistance to flow can stop the air-flow outside the cavity volume of leaf top to flow into described leaf top cavity volume from described channel of resistance to flow.
At one preferably or alternatively in embodiment, described the first guider is preced with the region division that end that trailing edge approaches the mounting edge of described turbine rotary axis approaches described turbine rotary axis outward the first adverse current groove, the integral shroud leading edge of described shrouded blade is provided with the second adverse current groove, and described the first adverse current groove and described the second adverse current groove are all positioned at the port that described channel of resistance to flow deviates from described leaf top cavity volume.
At one preferably or alternatively in embodiment, obturage platform and described the first double wedge three of described the first guider, described first is integral type structure, and described the second guider, described second platform of obturaging is integral type structure with described the second double wedge three.
The aero-turbine structure that the utility model provides, comprises the turbine runner seal structure that the arbitrary technological scheme of casing, guider, shrouded blade and the utility model provides, and described shrouded blade comprises integral shroud, blade, middle blade root and tenon.
Based on technique scheme, the utility model embodiment at least can produce following technique effect:
The turbine runner seal structure that the utility model provides, this structure is by the setting platform of obturaging, the mode of double wedge make to obturage platform and double wedge especially double wedge in turbine runner, formed and stopped, reduced the leakage flow that flows into and flow out integral shroud, reduced the disturbance to main flow fluid in turbine of leakage flow that turbine runner flows out away from the region of turbine rotary axis, further strengthened the effect of obturaging, being conducive to fluid flows away from the cleanliness in the region of turbine rotary axis at runner, also leakage flow and secondary aerodynamic loss have been reduced simultaneously, owing to can having effectively reduced the leakage flow of integral shroud away from surface and the casing radial clearance place of turbine rotary axis, strengthened the integral shroud effect of obturaging, so solved prior art exist casing and integral shroud more serious away from the radial surface gap location leakage flow of turbine rotary axis, cause the integral shroud poor technical problem of effect of obturaging, improved the streamlined characteristic of turbine runner away from the regions fluid of turbine rotary axis, can further improve turbine efficiency.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide further understanding of the present utility model, forms the application's a part, and schematic description and description of the present utility model is used for explaining the utility model, does not form improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 be in prior art in turbine turbine runner away from the cross-sectional schematic of position relationship between the region critical piece of turbine rotary axis;
A partial schematic sectional view of the turbine runner seal structure that Fig. 2 provides for the utility model embodiment 1;
A partial schematic sectional view of the turbine runner seal structure that Fig. 3 provides for the utility model embodiment 2;
A partial schematic sectional view of the turbine runner seal structure that the more excellent mode of execution that Fig. 4 is the utility model embodiment 3 provides;
Another partial schematic sectional view of the turbine runner seal structure that Fig. 5 provides for the utility model embodiment 3 preferred implementation;
Another partial schematic sectional view of the turbine runner seal structure that Fig. 6 provides for the utility model embodiment 3 preferred implementation;
A partial schematic sectional view of the turbine runner seal structure that Fig. 7 provides for the utility model embodiment 4;
A partial schematic sectional view of the turbine runner seal structure that Fig. 8 provides for 5 one kinds of mode of executions of the utility model embodiment;
A partial schematic sectional view of the turbine runner seal structure that Fig. 9 provides for the another kind of mode of execution of the utility model embodiment 5;
Reference character: 1, casing; 2, guider; 2a, the first guider; 2b, the second guider; 21, guider is preced with the mounting edge of trailing edge away from turbine rotary axis outward; 22, the mounting edge of turbine rotary axis is preced with trailing edge outward and approaches by guider; 220, first platform of obturaging; 221, the first double wedge; 201, the mounting edge of the outer nearly turbine rotary axis of crown grafting of guider is away from the surface of turbine rotary axis; 202, the mounting edge of the outer nearly turbine rotary axis of crown grafting of guider approaches the surface of turbine rotary axis; 223, the first adverse current groove; 24, guide vane; 26, hat in guider; 27, guider is preced with the mounting edge of leading edge away from turbine rotary axis outward; 28, the mounting edge of turbine rotary axis is preced with leading edge outward and approaches by guider; 280, second platform of obturaging; 281, the second double wedge; 282, the first water conservancy diversion groove; 3, rotor blade; 30, integral shroud; 31, integral shroud leading edge; 313, the second adverse current groove; 32, integral shroud trailing edge; 33, blade; 35, middle blade root; 37, tenon; 303A, sealing teeth; 303B, sealing teeth; 311, integral shroud leading edge is away from the surface of turbine rotary axis; 312, integral shroud leading edge approaches the surface of turbine rotary axis; 321, the second water conservancy diversion cut; 322, integral shroud trailing edge approaches the surface of turbine rotary axis; 4, honeycomb; 5, easily grind layer; 6, rotor exterior ring; 7, leaf top cavity volume; 80, arrow; 801, turbine runner; 99, turbine.
Embodiment
Can understand the distinctive points between content of the present utility model and the utility model and prior art with reference to accompanying drawing Fig. 1～Fig. 9 and word content below.Below by accompanying drawing and enumerate optional embodiments' more of the present utility model mode, the technical solution of the utility model (comprising optimal technical scheme) is described in further detail.It should be noted that: any technical characteristics in the present embodiment, any technological scheme is all one or more in technical characteristics or the optional technological scheme of plurality of optional, cannot exhaustive all alternative technical characteristicss of the present utility model and alternative technological scheme in order to describe succinct need in presents, also the mode of execution that is not easy to each technical characteristics all emphasizes that it is one of optional numerous embodiments, so those skilled in the art should know: arbitrary technological means that the utility model can be provided is replaced or any two or more technological means or technical characteristics that the utility model is provided combine mutually and obtain new technological scheme.Any technical characteristics in the present embodiment and any technological scheme all do not limit protection domain of the present utility model, protection domain of the present utility model should comprise those skilled in the art do not pay creative work thinkable any alternate embodiments and those skilled in the art any two or more technological means that the utility model is provided or technical characteristics combine mutually and the new technological scheme that obtains.
The utility model embodiment provides a kind of and can effectively reduce integral shroud away from the surface of turbine rotary axis and the turbine runner seal structure of casing radial clearance place leakage flow and the aero-turbine structure of this turbine runner seal structure is set.
Technological scheme the utility model being provided below in conjunction with Fig. 2～Fig. 9 is carried out more detailed elaboration.
Embodiment 1:
As shown in Figure 2, the turbine runner seal structure that the utility model embodiment provides, comprises the platform of obturaging (be preferably comprise first obturage platform 220 and second platform 280 of obturaging),
Wherein: the platform of obturaging is fixedly installed on outer the labeling of guider 2 in turbine runner 801, and at turbine in the radial direction, integral shroud 30 edges of the shrouded blade of obturaging in platform and turbine runner 801 exist alternating share between the two and have gap between the two.
In Fig. 2, only take the platform of obturaging, with respect to integral shroud 30 edges of the shrouded blade in turbine runner 801, be positioned at position further from turbine rotary axis as example.The turbine runner seal structure that the utility model provides, this structure stops interior formation of turbine runner 801 by the setting mode of the platform platform that makes to obturage of obturaging, reduced the leakage flow that flows into and flow out integral shroud 30, reduced the disturbance of turbine runner 801 away from the region of turbine rotary axis (in Fig. 2 take top area as example) convection cell, strengthened the effect of obturaging, being conducive to fluid flows away from the cleanliness in the region of turbine rotary axis at turbine runner 801, also leakage flow and secondary aerodynamic loss have been reduced simultaneously, so effectively reduced the leakage flow of integral shroud 30 away from surface and the casing radial clearance place of turbine rotary axis, strengthened integral shroud 30 effect of obturaging, improved the streamlined characteristic of turbine runner 801 away from the regional fluid of turbine rotary axis, can improve turbine 99 efficiency.
Embodiment 2:
As shown in Figure 3, the present embodiment and embodiment's 1 its difference are:
In the present embodiment, wheel runner seal structure also comprises double wedge, and double wedge preferably comprises the first double wedge 221 and the second double wedge 281 as shown in Figure 3.The present embodiment crowned tooth is fixedly installed on the platform of obturaging and approaches the surface of turbine rotary axis, the position of double wedge between the platform of obturaging approach the surface of turbine rotary axis and the integral shroud of shrouded blade 30 edges away from the gap between the surface of turbine rotary axis in.The platform of obturaging is preferably the end of the mounting edge that is fixedly installed on the nearly turbine rotary axis of the outer crown grafting of guider 2, double wedge is preferably as shown in Figure 3 and is fixedly installed on and obturages on platform, and double wedge extends away from the surperficial direction of turbine rotary axis towards integral shroud 30 edges that approach shrouded blade.
This turbine runner seal structure is by the setting platform of obturaging, the mode of double wedge make to obturage platform and double wedge (especially double wedge) stops interior formation of turbine runner 801, reduced the leakage flow that flows into and flow out integral shroud 30, reduced the disturbance of turbine runner 801 away from the region convection cell of turbine rotary axis, further strengthened the effect of obturaging, more being conducive to fluid flows away from the cleanliness in the region of turbine rotary axis at turbine runner 801, also leakage flow and secondary aerodynamic loss have been reduced simultaneously, so more effectively reduced the leakage flow of integral shroud 30 away from surface and the casing radial clearance place of turbine rotary axis, more strengthened integral shroud 30 effect of obturaging, improved the streamlined characteristic of turbine runner 801 away from the fluid of turbine rotary axis, can further improve turbine 99 efficiency.
Embodiment 3:
As shown in Figure 4, the present embodiment is substantially the same manner as Example 2, and its difference is: the outer profile size of the present embodiment crowned tooth dwindles away from the surperficial direction of turbine rotary axis gradually towards integral shroud 30 edges that approach shrouded blade.The double wedge root of this structure and the connection area of obturaging between platform are larger, and double wedge structural strength is higher.
As preferably or alternatively mode of execution of one, the end of the mounting edge of the nearly turbine rotary axis of the outer crown grafting of guider 2 approaches between the region of described turbine rotary axis (in Fig. 4, this region is positioned at the platform below of obturaging) and integral shroud 30 edges of shrouded blade and have gap on the axial direction of turbine 99.
This gap can form tortuous air-flow path, and tortuous air-flow path can change the direction of leakage flow after leakage flow flows through double wedge, reduces the impact that leakage flow causes main flow.
As preferably or alternatively mode of execution of one, guider 2 comprises the first guider 2a and the second guider 2b, and the platform of obturaging comprises first platform 220 and second platform 280 of obturaging of obturaging, wherein:
Double wedge comprises and is arranged on first obturage the first double wedge 221 on platform 220 and be arranged on second the second double wedge 281 of obturaging on platform 280.
The first guider 2a and the second guider 2b are two adjacent guiders 2, and the first guider 2a and the second guider 2b are separately positioned on front and the rear of the integral shroud 30 of same shrouded blade.
Herein, the integral shroud leading edge 31 of the first double wedge 221 and shrouded blade is all the smaller the better away from the gap between the surface of turbine rotary axis away from the integral shroud trailing edge 32 of gap between the two, the surface 311 of turbine rotary axis and the second double wedge 281 and shrouded blade, and object is in order to prevent the fluid leakage in sprue.
As preferably or alternatively mode of execution of one, the second guider 2b is preced with gap between the region that end that leading edge approaches the mounting edge of turbine rotary axis approaches turbine rotary axis (in Fig. 4, this region is positioned at second platform 280 belows of obturaging) and the integral shroud trailing edge 32 of shrouded blade outward and the integral shroud trailing edge 32 of the second double wedge 281 and shrouded blade is connected and forms guide channel away from the gap between the surface of turbine rotary axis.The maximum bearing of trend of guide channel is preferably with turbine runner 801 upper end wall inviscid flows to paralleling.Guide channel can change the direction of leakage flow, and then reduces the impact of leakage flow on turbine 99 interior main flows.
In Fig. 4, be also shown in: integral shroud trailing edge approaches the surface 322 of turbine rotary axis, the surface 322 that integral shroud trailing edge approaches turbine rotary axis is preferably plane.
As preferably or alternatively mode of execution of one, the second guider 2b is preced with the region that end that leading edge approaches the mounting edge of turbine rotary axis approaches turbine rotary axis (in Fig. 4, this region is positioned at second platform 280 belows of obturaging) outward and is provided with the first water conservancy diversion groove 282, what the integral shroud trailing edge 32 of shrouded blade was provided with that the second water conservancy diversion groove 321, the first water conservancy diversion grooves 282 and the second water conservancy diversion groove 321 be all positioned at guide channel goes out head piece place.Groove can play comparatively desirable leading role to the flow direction of leakage flow.The first water conservancy diversion groove 282 is preferably to be preced with the second guider 2b the surface smoothing transition that mounting edge that leading edge approaches turbine rotary axis approaches turbine rotary axis outward and to be connected.The second water conservancy diversion groove 321 is preferably with the integral shroud trailing edge 32 of shrouded blade and is connected away from the surface smoothing transition of turbine rotary axis.As preferably or alternatively mode of execution of one, obturage platform 220 and the first double wedge 221 threes of the first guider 2a, first are integral type structure.The second guider 2b, second obturages platform 280 and the second double wedge 281 threes for integral type structure.
Between each parts of integral structure, join strength is more reliable.Certainly, guider 2 with obturage between platform, obturaging also can adopt other modes that are fixedly connected with to be connected between platform and double wedge.
As preferably or alternatively mode of execution of one, the integral shroud leading edge of shrouded blade approach spacing between surface 312 and the turbine rotary axis of turbine rotary axis be not less than the first guider 2a be preced with outward surface that mounting edge that trailing edge approaches turbine rotary axis approaches turbine rotary axis at the upper end wall inviscid flow of turbine runner 801 to the elongated surfaces in direction (this direction is the indicated direction of arrow 80 shown in Fig. 4) and the spacing between turbine rotary axis.
In above-mentioned position relationship, position relationship between shrouded blade and the first guider 2a is the perfect condition in turbine working procedure, when turbine is during in static state, the integral shroud leading edge of shrouded blade approach spacing between surface 312 and the turbine rotary axis of turbine rotary axis generally can be less than the first guider 2a be preced with outward surface 222 that mounting edge that trailing edge approaches turbine rotary axis approaches turbine rotary axis at the upper end wall inviscid flow of turbine runner 801 to the elongated surfaces in direction (this direction is the indicated direction of arrow 80 shown in Fig. 4) and the spacing between turbine rotary axis.
As preferably or alternatively mode of execution of one, the first guider 2a is preced with gap between the region that end that trailing edge approaches the mounting edge of turbine rotary axis approaches turbine rotary axis (in Fig. 4, this region is positioned at first platform 220 belows of obturaging) and the integral shroud leading edge of shrouded blade outward and the integral shroud leading edge of the first double wedge 221 and shrouded blade is connected and forms channel of resistance to flow away from the gap between the surface of turbine rotary axis; Channel of resistance to flow can stop the air-flow outside leaf top cavity volume 7 to flow into leaf top cavity volume 7 as shown in Figure 6 from channel of resistance to flow.
Contrary with the effect of guide channel, channel of resistance to flow can provide resistance for the leakage flow outside leaf top cavity volume 7, avoid it from channel of resistance to flow, to flow into leaf top cavity volume 7, thereby can effectively reduce the leakage flow at integral shroud 30 and casing radial clearance place, strengthening integral shroud 30 effect of obturaging, improve the streamlined characteristic of turbine runner 801 away from the regional fluid of turbine rotary axis, and then improved turbine 99 efficiency.
As preferably or alternatively mode of execution of one, the first guider 2a is preced with the region that end that trailing edge approaches the mounting edge of turbine rotary axis approaches turbine rotary axis (this region be positioned at first obturage platform 220 belows) outward and is provided with the first adverse current groove 223 as shown in Figure 6, the integral shroud leading edge of shrouded blade is provided with the second adverse current groove 313, the first adverse current grooves 223 and the second adverse current groove 313 is all positioned at the port that channel of resistance to flow deviates from leaf top cavity volume 7.
The first adverse current groove 223 is specifically as follows curved surface as shown in Figure 4, also can be illustrated in figure 6 the combination of curved surface and plane.Certainly, the concrete shape of the first adverse current groove 223 and the second adverse current groove 313 can be according to the setting that needs of the effect of obturaging.The first adverse current groove 223 and the second adverse current groove 313 can stop the air-flow outside leaf top cavity volume 7 to flow into leaf top cavity volume 7 from channel of resistance to flow.
Below in conjunction with Fig. 4 and Fig. 5, concentrate the optimal technical scheme that illustrates that the present embodiment 3 provides:
As shown in Figure 4 and Figure 5, flow along the indicated direction of arrow 80 in high-energy fluid (for example: high-temperature fuel gas) region away from turbine rotary axis in turbine runner 801.
Guider is preced with mounting edge 22 that trailing edge approaches turbine rotary axis outward and is had first platform 220 of obturaging, first obturages on platform 220 is provided with the first double wedge 221, guider is preced with mounting edge 28 that leading edge edge approaches turbine rotary axis outward and is had second platform 280, the second of obturaging and obturage on platform 280 and be provided with the second double wedge 281 and the first water conservancy diversion groove 282.
There is integral shroud 30 on the leaf top of rotor blade 3, and integral shroud leading edge 31 and guider are preced with mounting edge 22 that trailing edge approaches turbine rotary axis outward and are formed and turn stationary fit.Integral shroud trailing edge 32 and guider are preced with mounting edge 28 that leading edge approaches turbine rotary axis outward and are formed and turn stationary fit, have reduced to turn the axial clearance of runner between quiet.
Integral shroud leading edge forms and levels off to the structure of hermetic seal away from the surface 311 of turbine rotary axis and the first double wedge 221, and the streamline flow of fluid is preced with surface engagement that mounting edge 22 that trailing edge approaches turbine rotary axis approaches turbine rotary axis outward and promoted by the surface 312 that integral shroud leading edge approaches turbine rotary axis and guider.Integral shroud trailing edge 32 has the second water conservancy diversion cut 321, the first water conservancy diversion grooves 282 away from the surface of turbine rotary axis and the second water conservancy diversion groove 321 forms guide channel, can effectively reduce the impact of leakage flow incident direction on main flow.
Embodiment 4:
As shown in Figure 7, the present embodiment is substantially the same manner as Example 2, its difference is: the present embodiment crowned tooth 221 is fixedly installed on integral shroud 30 edges of shrouded blade away from the surface of turbine rotary axis, now, the surperficial direction that double wedge 221 approaches turbine rotary axis towards the approaching platform 220 of obturaging is extended.In Fig. 7, only take integral shroud 30 edges, away from the surface of turbine rotary axis, at being positioned in the radial direction of the turbine platform 220 of obturaging, approach above turbine rotary axis surperficial as example.
Embodiment 5:
As shown in Figure 8 and Figure 9, the present embodiment is substantially the same manner as Example 1, and its difference is: the platform of obturaging in the present embodiment (platform of obturaging in Fig. 8 comprise first obturage platform 220 and second platform 280 of obturaging) with respect to integral shroud 30 edges of the shrouded blade in turbine runner be positioned at more approach turbine rotary axis position.
In Fig. 9, only take first, obturage platform 220 as example, in Fig. 9, only first platform 220 of obturaging is positioned at respect to integral shroud 30 edges of the shrouded blade in turbine runner the position that more approaches turbine rotary axis, as second platform 280 of obturaging in Fig. 8 is also positioned at respect to integral shroud 30 edges of the shrouded blade in turbine runner the position that more approaches turbine rotary axis.
As one preferred embodiment, double wedge (in Fig. 9 only take the first double wedge 221 as example) is fixedly installed on the platform of obturaging away from the surface of turbine rotary axis, and double wedge position is between the platform of obturaging approaches the gap between the surface of turbine rotary axis away from the surface of turbine rotary axis and the integral shroud of shrouded blade 30 edges in.
Such scheme also can effectively reduce the leakage flow at integral shroud 30 and casing radial clearance place, has strengthened integral shroud 30 effect of obturaging, and has improved the streamlined characteristic of turbine runner 801 away from the regional fluid of turbine rotary axis, can improve turbine efficiency.
It should be noted that: above-described embodiment 1～4 crowned tooth with obturage structure and the double wedge of platform and the relative position relation of the platform of obturaging all can be applied or equivalents after be for example applied to, among the present embodiment 5: the integral shroud edge that double wedge also can be fixedly installed on shrouded blade approaches on the surface of turbine rotary axis.
The aero-turbine structure that the utility model embodiment provides, comprise that casing 1, guider 2, shrouded blade are the turbine runner seal structure that rotor blade 3 and the arbitrary technological scheme of the utility model provide as shown in Figure 4, shrouded blade is that rotor blade 3 comprises integral shroud 30, blade 33, middle blade root 35 and tenon 37.This aero-turbine structure can also comprise the miscellaneous parts such as honeycomb 4, easy mill layer 5 and rotor exterior ring 6.
Above-mentioned arbitrary technological scheme disclosed in the utility model unless otherwise stated, if it discloses number range, so disclosed number range is preferred number range, any it should be appreciated by those skilled in the art: preferred number range is only the obvious or representative numerical value of technique effect in many enforceable numerical value.Because numerical value is more, cannot be exhaustive, so the utility model just discloses part numerical value to illustrate the technical solution of the utility model, and the above-mentioned numerical value of enumerating should not form the restriction of the utility model being created to protection domain.
If used the words such as " first ", " second " to limit component herein, those skilled in the art should know: the use of " first ", " second " is only used to be convenient to describe above component are distinguished as not having outside Stated otherwise, and above-mentioned word does not have special implication.
Simultaneously, if above-mentioned the utility model discloses or has related to component or the structural member of connection fastened to each other, so, unless otherwise stated, be fixedly connected with and can be understood as: can dismantle and be fixedly connected with (for example using bolt or screw to connect), also can be understood as: non-removable being fixedly connected with (for example rivet, weld), certainly, connection fastened to each other also can for example, be replaced (obviously cannot adopt except integrally formed technique) by integral type structure (use casting technique is integrally formed to be created).
In addition, in the disclosed arbitrary technological scheme of above-mentioned the utility model applied for the term that represents position relationship or shape unless otherwise stated its implication comprise and its approximate, similar or approaching state or shape.Arbitrary parts that the utility model provides can be both to be assembled by multiple independent constituent elements, the produced separate part of the technique that also can be one of the forming.
Finally should be noted that: above embodiment is only in order to illustrate that the technical solution of the utility model is not intended to limit; Although the utility model is had been described in detail with reference to preferred embodiment, those of ordinary skill in the field are to be understood that: still can modify or part technical characteristics is equal to replacement embodiment of the present utility model; And not departing from the spirit of technical solutions of the utility model, it all should be encompassed in the middle of the technological scheme scope of the utility model request protection.
Claims (13)
1. a turbine runner seal structure, is characterized in that, comprises the platform of obturaging, wherein:
The guider that the described platform of obturaging is fixedly installed in turbine runner is labeled outward;
There is alternating share between the two and have gap between the two in obturage at turbine in the radial direction, the integral shroud edge of the shrouded blade in platform and described turbine runner.
2. turbine runner seal structure according to claim 1, is characterized in that, described turbine runner seal structure also comprises double wedge, wherein:
The platform of obturaging described in described double wedge is fixedly installed on approaches the surface of described turbine rotary axis or is fixedly installed on the integral shroud edge of described shrouded blade away from the surface of described turbine rotary axis, described double wedge position between the described platform of obturaging approach the surface of described turbine rotary axis and the integral shroud edge of described shrouded blade away from the gap between the surface of described turbine rotary axis in; Or,
The platform of obturaging described in described double wedge is fixedly installed on approaches the surface of described turbine rotary axis away from the surface of described turbine rotary axis or the integral shroud edge that is fixedly installed on described shrouded blade, described double wedge position is between the described platform of obturaging approaches the gap between the surface of described turbine rotary axis away from the surface of described turbine rotary axis and the integral shroud edge of described shrouded blade in.
3. turbine runner seal structure according to claim 2, it is characterized in that, the described platform of obturaging is fixedly installed on the end of the mounting edge of the outer nearly described turbine rotary axis of crown grafting of described guider, described in described double wedge is fixedly installed on, obturage on platform, and described double wedge extends away from the surperficial direction of described turbine rotary axis towards the integral shroud edge that approaches described shrouded blade.
4. turbine runner seal structure according to claim 3, is characterized in that, the outer profile size of described double wedge dwindles away from the surperficial direction of described turbine rotary axis gradually towards the integral shroud edge that approaches described shrouded blade.
5. turbine runner seal structure according to claim 3, it is characterized in that, the end of the mounting edge of the outer nearly described turbine rotary axis of crown grafting of described guider approaches between the region of described turbine rotary axis and the integral shroud edge of described shrouded blade and have gap on the axial direction of described turbine.
6. turbine runner seal structure according to claim 5, is characterized in that, described guider comprises the first guider and the second guider, described in the platform of obturaging comprise first platform and second platform of obturaging of obturaging, wherein:
Described double wedge comprises and is fixedly installed on described first obturage the first double wedge on platform and be fixedly installed on described second the second double wedge of obturaging on platform;
Described first platform of obturaging is arranged on described the first guider and is preced with trailing edge outward and approaches the end of the mounting edge of described turbine rotary axis, and described the first double wedge extends away from the surperficial direction of described turbine rotary axis towards the integral shroud leading edge that approaches described shrouded blade;
Described second platform of obturaging is arranged on described the second guider and is preced with leading edge outward and approaches the end of the mounting edge of described turbine rotary axis, and described the second double wedge extends away from the surperficial direction of described turbine rotary axis towards the integral shroud trailing edge that approaches described shrouded blade.
7. turbine runner seal structure according to claim 6, is characterized in that, the gap that described the second guider is preced with outward between the integral shroud trailing edge of leading edge and described shrouded blade forms guide channel.
8. turbine runner seal structure according to claim 7, it is characterized in that, described the second guider is preced with the region division that end that leading edge approaches the mounting edge of described turbine rotary axis approaches described turbine rotary axis outward the first water conservancy diversion groove, the integral shroud trailing edge of described shrouded blade is provided with the second water conservancy diversion groove, and what described the first water conservancy diversion groove and described the second water conservancy diversion groove were all positioned at described guide channel goes out head piece place.
9. turbine runner seal structure according to claim 6, it is characterized in that, the integral shroud leading edge of described shrouded blade approach spacing between surface and the described turbine rotary axis of described turbine rotary axis be not less than described the first guider be preced with outward surface that mounting edge that trailing edge approaches described turbine rotary axis approaches described turbine rotary axis at the upper end wall inviscid flow of described turbine runner to the elongated surfaces in direction and the spacing between described turbine rotary axis.
10. according to the arbitrary described turbine runner seal structure of claim 6-9, it is characterized in that, described the first guider is preced with that end that trailing edge approaches the mounting edge of described turbine rotary axis approaches gap between the region of described turbine rotary axis and the integral shroud leading edge of described shrouded blade and the integral shroud leading edge of described the first double wedge and described shrouded blade is connected and forms channel of resistance to flow away from the gap between the surface of described turbine rotary axis outward; Described channel of resistance to flow can stop the air-flow outside the cavity volume of leaf top to flow into described leaf top cavity volume from described channel of resistance to flow.
11. turbine runner seal structures according to claim 10, it is characterized in that, described the first guider is preced with the region division that end that trailing edge approaches the mounting edge of described turbine rotary axis approaches described turbine rotary axis outward the first adverse current groove, the integral shroud leading edge of described shrouded blade is provided with the second adverse current groove, and described the first adverse current groove and described the second adverse current groove are all positioned at the port that described channel of resistance to flow deviates from described leaf top cavity volume.
12. according to the arbitrary described turbine runner seal structure of claim 6-9, it is characterized in that, described the first guider, described first is obturaged platform and described the first double wedge three for integral type structure, and described the second guider, described second platform of obturaging is integral type structure with described the second double wedge three.
13. 1 kinds of aero-turbine structures, is characterized in that, comprise the arbitrary described turbine runner seal structure of casing, guider, shrouded blade and claim 1-12, and described shrouded blade comprises integral shroud, blade, middle blade root and tenon.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320812074.6U CN203584475U (en) | 2013-12-11 | 2013-12-11 | Turbine runner sealing structure and aeroengine turbine structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320812074.6U CN203584475U (en) | 2013-12-11 | 2013-12-11 | Turbine runner sealing structure and aeroengine turbine structure |
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| Publication Number | Publication Date |
|---|---|
| CN203584475U true CN203584475U (en) | 2014-05-07 |
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| CN201320812074.6U Expired - Lifetime CN203584475U (en) | 2013-12-11 | 2013-12-11 | Turbine runner sealing structure and aeroengine turbine structure |
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| CN (1) | CN203584475U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110300838A (en) * | 2017-02-16 | 2019-10-01 | 通用电气公司 | Heat structure for outer diameter mount type turbo blade |
| CN111691927A (en) * | 2020-05-22 | 2020-09-22 | 哈尔滨工业大学 | Turbine and turbine blade tip clearance seal structure |
| CN114776389A (en) * | 2022-03-16 | 2022-07-22 | 北京航空航天大学 | Shrouded turbine with flange plate step casing |
-
2013
- 2013-12-11 CN CN201320812074.6U patent/CN203584475U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110300838A (en) * | 2017-02-16 | 2019-10-01 | 通用电气公司 | Heat structure for outer diameter mount type turbo blade |
| CN110300838B (en) * | 2017-02-16 | 2022-09-16 | 通用电气公司 | Thermal structure for outer diameter mounted turbine blades |
| CN111691927A (en) * | 2020-05-22 | 2020-09-22 | 哈尔滨工业大学 | Turbine and turbine blade tip clearance seal structure |
| CN114776389A (en) * | 2022-03-16 | 2022-07-22 | 北京航空航天大学 | Shrouded turbine with flange plate step casing |
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| GR01 | Patent grant | ||
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Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: AECC COMMERCIAL AIRCRAFT ENGINE Co.,Ltd. Address before: 201108 Shanghai city Minhang District Lotus Road No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
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| CP03 | Change of name, title or address | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140507 |
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