CN202811083U - Sealing element - Google Patents
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- CN202811083U CN202811083U CN 201220349162 CN201220349162U CN202811083U CN 202811083 U CN202811083 U CN 202811083U CN 201220349162 CN201220349162 CN 201220349162 CN 201220349162 U CN201220349162 U CN 201220349162U CN 202811083 U CN202811083 U CN 202811083U
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- sealing
- firing chamber
- turbine nozzle
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Abstract
The utility model provides a sealing element which is provided with a gap jointly limited by a combustion chamber and a turbine nozzle for sealing, wherein the combustion chamber is provided with a first seal surface, the turbine nozzle is provided with a second seal surface, the sealing element is made from an elastic high temperature-resistant material, the sealing element leastways comprises a first seal means and a second seal means, the first seal means is used for inwards sealing the first seal surface and the second seal surface, and the second seal means is used for outwards sealing the first seal surface and the second seal surface. According to the sealing element, the good tightness can be provided, the hot gas can not pass to the external part of the combustion chamber, and cracks of the sealing element since the sealing element is exposed under a high temperature can be avoided; and an arc seal part of the sealing element can track the movement of a turbine nozzle section within an operation period to allow the combustion chamber and the high-pressure worm wheel to relatively move due to the vibration and the different thermal expansion. The sealing element disclosed by the utility model is simple in structure, and easy to install and replace.
Description
Technical field
The utility model relates to a kind of Sealing, relates in particular to the Sealing that the end of a kind of outlet end to the firing chamber and turbine nozzle seals.
Background technique
With reference to figure 1, Fig. 1 shows the annular combustion chamber 10 of the turbo machine such as airplane turbine airscrew engine or turbogenerator, and this combustion chamber placement is in the downstream of compressor and Diffuser (not shown) and be arranged in the upstream of the inlet nozzle 12 of high-pressure turbine 10.
Doughnut end wall 18 has the opening 28 that passes through together for the air of gas compressor and fuel that sparger 30 is carried, and sparger 30 is fastened on the frame 22.
Nozzle 12 is fastened on the downstream of firing chamber 10 and comprises interior ring-shaped platform 32 and outer ring platform 34 by suitable device, the outside ring-shaped platform 34 interior extensions of interior ring-shaped platform 32, interior ring-shaped platform 32 and outer ring platform 34 link together by radially blade 36 roughly.The downstream end of the outer platform 34 of nozzle 12 and the outer wall 16 of firing chamber 10 axially aligns, and the downstream end of the inwall 14 of inner platform 32 and firing chamber 10 axially aligns.
The platform 32 of nozzle 12 and 34 and interior annular flange flange 24 and the outer annular flanges 20 of firing chamber jointly limit two annular spaces 38, space and the external space namely, each space all at one end to the inside of firing chamber 10 open wide and all the other end be installed in platform 32,34 and flange 20,24 between seal arrangement 40,40 ' seal.
By the opening 28 on the end wall 18 and present to firing chamber 10 (arrow 42), the remaining part air-flow is presented to interior annular overcurrent part 44 and the outer ring overcurrent part 46 (arrow 48) of process around 10 in the firing chamber by a part of air-flow of the gas compressor supply that is positioned at the upstream.
Interior overcurrent part 44 is formed between the inner housing 26 and inwall 14 of firing chamber 10, and the air that passes through from this space enters in the firing chamber 10 for cooled inner wall 14 via the hole 50 of inwall 14; Also the flow through hole 52 of inward flange 24 of firing chamber 10 of interior overcurrent part 44 is used for inner sealing device 40 ' that cooling is connected with the inwall 14 of firing chamber 10 and the periphery of inward flange 24.Then, the part of the air by inward flange 24 by via the cavity in the blade 36 of nozzle radially outwards by passing nozzle 12.
Outer overcurrent part 46 is formed between the frame 22 and outer wall 16 of firing chamber 10, the sub-fraction of the air that passes through from this space is flowed through hole 50 on the outer wall 16 with cooling outer wall 16, also has sub-fraction to flow through hole 52 on the outward flange 20 with interior week of cooling outer sealing device 40 and flange 20.
Fig. 2 is the view of the larger proportion of outer sealing device 40.Outer sealing device 40 comprises a plurality of slats 54, and the pad lid is circumferentially arranged and be equipped with to these slats 54 adjacent to each other around the longitudinal axis edge of firing chamber 10.Each slat 54 is formed by the tablet of circumferential orientation, and it extends in upstream roughly when installation in position and extends internally.Be riveted to nozzle section 12 fastening slats 54 by the middle part with slat 54, and the outer periphery 56 of slat 54 are bearing on the radial surface at cylindrical shape edge 57 of flange 20.
The platform 34 of the section of nozzle 12 comprises two radial walls 58,60 at upstream extremity, and these two radial walls are spaced apart from each other in the axial direction and are used for installing outer sealing device 40.These walls 58,60 comprise the axial bore that the fastening rivet 62 of a plurality of slats 54 passes through.
The wall that is positioned at the upstream 58 of platform 34 defines annular space 38 jointly with the fastening flange 20 of wall 16.Outer sealing device 40 is fixed between two walls 58,60.Outer sealing device 40 is bearing on the downstream radial surface of wall 58 and is subject to being installed in spring 64 upstream pushings between the wall 60 of outer sealing device 40 and platform 34.
Inner sealing device 40 ' and outer sealing device 40 are similar.Yet as mentioned above, the sealing of the enforcement of these devices is unsafty.Particularly, on firing chamber and turbine nozzle, its sealing is relatively poor along the circle line bearing for above-mentioned seal arrangement; When the vibration of bearing with high-pressure turbine when the firing chamber is relative to each other moved with different thermal expansions, might have the outside that hot gas passes to the firing chamber, thereby cause described component exposure the risk in crack under high-temperature, to occur; The complex structure of sealing device; And the sealing device also is not easy to install and replace.
The model utility content
The utility model provides a kind of Sealing, it is arranged between the entrance end of the outlet end of firing chamber and turbine nozzle, described Sealing is made by flexible exotic material, it comprises the first hermetic unit at least, the second hermetic unit and the 3rd hermetic unit, wherein, described the second hermetic unit radially is arranged in the outside of described the first hermetic unit, relatively described the first hermetic unit of described the 3rd hermetic unit and described the second hermetic unit are axially arranged, one of them of the outlet end of described the first hermetic unit and described the second hermetic unit and described firing chamber and the entrance end of described turbine nozzle connects, and another of the entrance end of the outlet end of described the 3rd hermetic unit and described firing chamber and described turbine nozzle connects.
Preferably, one of them face of the outlet end of described the first hermetic unit and described the second hermetic unit and described firing chamber and the entrance end of described turbine nozzle connects contiguously, and another face of the entrance end of the outlet end of described the 3rd hermetic unit and described firing chamber and described turbine nozzle connects contiguously.
Preferably, described the first hermetic unit and described the second hermetic unit are mutually symmetrical.
Preferably, the outer surface of described the first hermetic unit, described the second hermetic unit and/or described the 3rd hermetic unit is curved.
Preferably, described Sealing is annular.
Selectively, described Sealing is arc.
Preferably, described Sealing also is limited with the cooling impact opening, so that the gas outside the described firing chamber cools off described Sealing through described cooling impact opening.
Preferably, has wear resistant coating at least one the surface of described the first hermetic unit, the second hermetic unit and the 3rd hermetic unit.
Particularly, described wear resistant coating is formed by the nickel-base material alloy.
The utility model discloses a kind of Sealing, it is arranged in the gap that is jointly limited by firing chamber and turbine nozzle in order to sealing to be provided, described firing chamber provides the first sealing surfaces, described turbine nozzle provides the second sealing surfaces, described Sealing is made by flexible exotic material, it comprises the first hermetic unit, the second hermetic unit, the 3rd hermetic unit and the 4th hermetic unit, wherein, described the first hermetic unit and described the 3rd hermetic unit are axially arranged symmetrically, described the second hermetic unit and described the 4th hermetic unit are axially arranged symmetrically, described the second hermetic unit radially is arranged in the outside of described the first hermetic unit, and described the 4th hermetic unit radially is arranged in the outside of described the 3rd hermetic unit; Wherein, one of them of described the first hermetic unit and described the second hermetic unit and described the first sealing surfaces and described the second sealing surfaces connects, and another of described the 3rd hermetic unit and described the 4th hermetic unit and described the first sealing surfaces and described the second sealing surfaces connects.
Preferably, one of them face of described the first hermetic unit and described the second hermetic unit and described the first sealing surfaces and described the second sealing surfaces connects contiguously, and another face of described the 3rd hermetic unit and described the 4th hermetic unit and described the first sealing surfaces and described the second sealing surfaces connects contiguously.
Preferably, described the first hermetic unit and described the second hermetic unit are symmetrical, and described the 3rd hermetic unit and described the 4th hermetic unit are symmetrical.
More preferably, described the first hermetic unit and described the 3rd hermetic unit are symmetrical, and described the second hermetic unit and described the 4th hermetic unit are symmetrical.
Particularly, described the first hermetic unit and described the 3rd hermetic unit form the inside roughly V-arrangement of opening or C shape roughly.
Particularly, the roughly V-arrangement of described the second hermetic unit and described the 4th hermetic unit formation outward opening or roughly C shape.
Particularly, described Sealing roughly is the figure of eight or " X " font.
Optionally, described the first hermetic unit and described the second hermetic unit partly are connected to described the 3rd hermetic unit and the 4th hermetic unit by intermediate seal.
Particularly, described intermediate seal part undulate.
Particularly, described intermediate seal part roughly is O shape, U-shaped, V-arrangement, M shape or W shape.
The utility model discloses a kind of Sealing, it is arranged in the gap that is jointly limited by firing chamber and turbine nozzle in order to sealing to be provided, described firing chamber provides the first sealing surfaces, described turbine nozzle provides the second sealing surfaces, described Sealing is made by flexible exotic material, it comprises that at least first surface contact hermetic unit contacts hermetic unit with second, wherein, described first surface contact hermetic unit is used for inner ground and face seals described the first sealing surfaces and described the second sealing surfaces contiguously, and described second contact hermetic unit is used for outer ground and face seals described the first sealing surfaces and described the second sealing surfaces contiguously.
The utlity model has following technique effect:
The first, traditional Sealing along the circle line bearing on firing chamber and turbine nozzle, and at least one side of Sealing of the present utility model be by means of " dual torus " surface bearing on firing chamber and turbine nozzle.Thereby the utility model can provide good sealing, stops hot gas to pass to the outside of firing chamber, avoids described component exposure under high temperature and the crack occurs;
The second, the arc hermetic unit of the described Sealing movement that can follow the trail of during operation described turbine nozzle section, thus allow vibration that firing chamber and high-pressure turbine bear with different thermal expansions and relative to each other mobile;
Three, the disclosed Sealing of the utility model is simple in structure;
Four, the disclosed Sealing of the utility model is easy to install and replace.
Description of drawings
In order to explain the utility model, its illustrative embodiments will be described with reference to the drawings hereinafter, in the accompanying drawing:
Fig. 1 shows the schematically circumferential half sectional view of the firing chamber of turbo machine of prior art and turbine nozzle, and wherein seal arrangement is installed between firing chamber and the turbine nozzle;
Fig. 2 shows the part enlarged view of Fig. 1;
Fig. 3 schematically shows the sectional view of the Sealing of the first mode of execution of the present utility model;
The Sealing that Fig. 4 schematically shows the first mode of execution of the present utility model is installed in schematic half sectional view between firing chamber and the turbine nozzle with the first mounting type;
The Sealing that Fig. 5 schematically shows the first mode of execution of the present utility model is installed in schematic half sectional view between firing chamber and the turbine nozzle with the second mounting type;
Fig. 6 schematically shows the sectional view of the Sealing of the utility model the second mode of execution;
The Sealing that Fig. 7 schematically shows the second mode of execution of the present utility model is installed in the schematic half sectional view between firing chamber and the turbine nozzle;
Fig. 8 schematically shows the sectional view of the Sealing of the third mode of execution of the present utility model;
Fig. 9 schematically shows the segmentation structure of the Sealing of the utility model the second mode of execution;
Similar features among the different figure is by similar reference character indication.
Embodiment
Fig. 3 discloses outside seal may 100, the inner seal liner 100 ' of the utility model the first mode of execution.Particularly, the seal 100,100 ' all has the first hermetic unit 102 that is little arc, the 3rd hermetic unit 106 that is the second hermetic unit 104 of little arc and is large arc, wherein, the first hermetic unit 102 and the second hermetic unit 104 are arranged symmetrically, the 3rd hermetic unit 106 is equivalent to the attachment portion of the first hermetic unit 102 and the second hermetic unit 104, by this, the first hermetic unit 102, the second hermetic unit 104 and the 3rd hermetic unit 106 link together smoothly.Like this, from perspective view, the annular that the seal 100,100 ' all is integrated, if Sealing 100,100 ' is segmented, then it is arc; From sectional view, each Sealing 100,100 ' two ends have respectively to Sealing 100,100 ' the curling trend in inside, thereby make Sealing 100,100 ' cross section roughly be the ear shape, if do not consider this curlingly, Sealing 100,100 ' sectional shape then are similar to C shape.The seal 100,100 ' is made by flexible exotic material, and this exotic material is generally metallic material, such as marmem.
As shown in Figure 4, outside seal may 100, inner seal liner 100 ' are installed between firing chamber 40 and the turbine nozzle 50 with the first mounting type.The end of firing chamber 40 has radially the first outer end wall part 42 of extending and from terminal axially extended the second outer end wall 44 parts of the first outer end wall part 42, similarly, the end of turbine nozzle 50 has radially all round end wall portion 54 of the 3rd outer end wall part 52 of extending and axially extended the.Like this, the 3rd outer end wall part 52 of the first outer end wall part 42 of firing chamber 40 and the second outer end wall part 44 and turbine nozzle 50 and all round end wall portion 54 defines the outer ring gap jointly, the direction of the first outer end wall part 42 in the downstream of firing chamber 40 defines the first outer seal surface S1, correspondingly, the direction of the 3rd outer end wall part 52 in the upstream of turbine nozzle 50 defines the second outer seal surface S2.
Outside seal may 100 is contained in the outer ring gap, wherein, on the first outer end wall part 42 of the first hermetic unit 102 and the second hermetic unit 104 butt firing chambers 40 to seal the first outer seal surface S1, simultaneously, on the 3rd outer end wall part 52 of the 3rd hermetic unit 106 butt turbine nozzles 50 to seal the second outer seal surface S2.By finding out among Fig. 4, in the time of in outside seal may 100 is installed in above-mentioned outer ring gap, the second hermetic unit 104 radially is positioned at the outside of the first hermetic unit 102, and 106 of the 3rd hermetic units axially are positioned at the downstream of the first hermetic unit 102 and the second hermetic unit 104.
Because the characteristic of the elastically deformable of outside seal may 100, even motor because of thermal expansion relative displacement occurs in the end of run duration firing chamber 40 and the end of turbine nozzle 50, thereby can upwards being out of shape the mode that contacts with face reliably with the footpath in the axial direction, this first hermetic unit 102, the second hermetic unit 104 and the 3rd hermetic unit 106 seal the first outer seal surface S1 and the second outer seal surface S2.
Similarly, also be limited with interior annular space between firing chamber 40 and the turbine nozzle 50, inner seal liner 100 ' is accommodated in the inner in the annular space.Because the structure of inner seal liner 100 ' is identical with outside seal may 100, mounting type and elastic characteristic etc. are also all identical, so do not repeat them here.
As shown in Figure 5, above-mentioned outside seal may 100, inner seal liner 100 ' can be installed between firing chamber 40 and the turbine nozzle 50 with the second mounting type, describe as an example of the mounting type of outside seal may 100 example at this.Outside seal may 100 is contained in the outer ring gap, wherein, the mode that contacts with face on the 3rd outer end wall part 52 of the first hermetic unit 102 and the second hermetic unit 104 butt turbine nozzles 50 seals the second outer seal surface S2, simultaneously, mode with the face contact on the first outer end wall part 42 of the 3rd hermetic unit 106 butt firing chambers 40 seals the first outer seal surface S1, by finding out among Fig. 5, in the time of in outside seal may 100 is installed in above-mentioned outer ring gap, the second hermetic unit 104 radially is positioned at the outside of the first hermetic unit 102, and 106 of the 3rd hermetic units axially are positioned at the upstream of the first hermetic unit 102 and the second hermetic unit 104.
Fig. 6 discloses outside seal may 200, the inner seal liner 200 ' of the utility model the second mode of execution.Only be described as an example of outside seal may 200 example at this.This outside seal may 200 has the first hermetic unit 202, the second hermetic unit 204, the 3rd hermetic unit 206 and the 4th hermetic unit 208, and other three hermetic units are kept apart observation, and a remaining hermetic unit is curved; The first and the 3rd hermetic unit is kept apart observation, and the second remaining hermetic unit and the 4th hermetic unit are rendered as on the whole has outwardly open roughly O shape (if opening is larger, then being rendered as outwardly open C shape); The second and the 4th hermetic unit is kept apart observation, and the first remaining hermetic unit and the 3rd hermetic unit are rendered as the roughly O shape (if opening is larger, then being rendered as the C shape to inner opening) that has to inner opening on the whole; This outside seal may 200 of whole observation, then this outside seal may 200 roughly is 8-shaped.
As shown in Figure 7, outside seal may 200 is installed in the outer ring gap of firing chamber 40 and turbine nozzle 50, and inner seal liner 200 ' is installed in the interior annular space of firing chamber 40 and turbine nozzle 50.Because the mounting type of outside seal may 200 and inner seal liner 200 ' is similarly, so still be described as an example of outside seal may 200 example at this.The first hermetic unit 202 and the second hermetic unit 204 fit to the first outer end wall part 42 of firing chamber 40 to seal the first outer seal surface, and the 3rd hermetic unit 206 and the 4th hermetic unit 208 fit to the 3rd outer end wall part 52 of turbine nozzle 50 to seal the second outer seal surface.Like this, diametrically, the second hermetic unit 204 is arranged in the outside of the first hermetic unit 202, and the 4th hermetic unit 208 is arranged in the outside of the 3rd hermetic unit 206; In the axial direction, the 3rd hermetic unit 206 is arranged in the downstream with respect to the first hermetic unit 202, and the 4th hermetic unit 208 relative the second hermetic units 204 are arranged the downstream.By this, the first hermetic unit 202 and the second hermetic unit 204 all with the first outer seal surface face butt contiguously, simultaneously, the 3rd hermetic unit 206 and the 4th hermetic unit 208 all with the second outer seal surface face butt contiguously, therefore, certain hermetic unit all formed double seal at each sealing surfaces, even can not affect sealing effect owing to long term wear or other reasons damage also like this.
In addition, because this outside seal may 200 is to be made by flexible exotic material equally, so its also with aforesaid Sealing 100 the same characteristics with resiliently deformable, therefore, even motor because of thermal expansion relative displacement occurs in the end of run duration firing chamber 40 and the end of turbine nozzle 50, thereby this first hermetic unit 202, the second hermetic unit 204, the 3rd hermetic unit 206 and the 4th hermetic unit 208 can upwards be out of shape reliably with the footpath in the axial direction and face seals the first outer seal surface S1 and the second outer seal surface S2 contiguously.
Referring to Fig. 8, it shows the sectional view of the Sealing 300 of the third mode of execution of the present utility model.The seal 300 roughly is X-shaped on the whole, the first hermetic unit 302 and the 3rd hermetic unit 306 form the roughly V font that Open Side Down, the second hermetic unit 304 and the 4th hermetic unit 308 form the roughly V font of opening upwards, and four hermetic units by two roughly the summit of V-arrangement shape link together, each roughly the open end of V font all be circular-arc and have to the curling trend of open interior of V font roughly.
Like this, when the seal 300 is installed on the outer ring gap that the end by the end of firing chamber 40 and turbine nozzle 50 limits as outside seal may, in the axial direction, the 3rd hermetic unit 306 and the 4th hermetic unit 308 lay respectively at the downstream of the first hermetic unit 302 and the second hermetic unit 304, diametrically, the second hermetic unit 304 and the 4th hermetic unit 308 are positioned at the outside of the first hermetic unit 302 and the 3rd hermetic unit 306.
Referring to Fig. 9, this there is shown Sealing mentioned above 200,200 ' segmentation structure, this means, if seal the annular space fully, then at the Sealing 200,200 ' that upwards needs the multistage arc week, can use between each section such as pad to connect, can be provided with on the pad for the boss of circumferentially locating to prevent from causing because of vibration the circumferential play of Sealing.More preferably, it is preferably identical with the quantity of turbine nozzle the quantity of arc seals upwards to be set week.Can understand easily, Sealing adopts the integral type loop configuration or the segmented arcuate structure depends on the conditions such as manufacturing and assembling.Be appreciated that also all Sealings mentioned above all can adopt segmentation structure.
It will be appreciated by those skilled in the art that, above-mentioned Sealing 200,200 ' and 300 can also have the intermediate seal part, namely, this intermediate seal partly is arranged between two C shape shapes (or two O shape shapes with opening) or two the V-arrangement shapes, in other words, it is upper but partly be connected on the second hermetic unit 204 (or 304) and the 4th hermetic unit 208 (or 308) by this intermediate seal that the first hermetic unit 202 (or 302) and the 3rd hermetic unit 206 (or 306) are not directly connected to the second hermetic unit 204 (or 304) and the 4th hermetic unit 208 (or 308).Can make like this radial length length of side of Sealing.The intermediate seal part can be U-shaped, V-arrangement, M shape or W shape; Also can be a plurality of M shapes or a plurality of W shape, it be wavy like this intermediate seal partly to be rendered as.The intermediate seal part can also be one or more O shapes, if the axial width of the exterior contour of these one or more O shapes is identical with width between the first hermetic unit 202 (or 302) and the 4th hermetic unit 208 (or 308), then this intermediate seal part can also play the 3rd layer seal action.Be appreciated that above-mentioned Sealing with intermediate seal part can be integrally formed.
Be appreciated that Sealing mentioned above 100 has one-sided double-layer seal effect, other Sealings are such as 200,200 ' and the 300 double-layer seal effects that all have a bilateral.In fact, according to essence of the present invention, the Sealing that has greater than two-layer multi-layer sealed effect is easy to also realize that for example aforesaid Sealing 200 can partly reach more multi-layered sealing by the intermediate seal of O shape.
Also should be appreciated that, can also be limited with the cooling impact opening on the disclosed Sealing of the utility model, simultaneously, also correspondingly be limited with the cooling impact opening on the second outer end wall part of firing chamber and the first outer end wall part of turbine nozzle, by the cooperation of these cooling impact openings, the sub-fraction in the air-flow of the by-pass air duct outside the firing chamber can be cooled off impact opening via these end of Sealing, firing chamber and the end of turbine nozzle are cooled off.
Those skilled in the art also should be appreciated that for wear prevention, can be provided with wear resistant coating on the outer surface of the part of each Sealing butt sealing surfaces, and typically, this wear resistant coating can be formed by the nickel-base material alloy.
The utility model is limited to the illustrative embodiments that presents never in any form in specification and accompanying drawing.All combinations of the mode of execution that illustrates and describe (part) are interpreted as clearly to incorporate within this specification and be interpreted as clearly and fall in the scope of the present utility model.And in the scope of the present utility model of summarizing such as claims, a lot of distortion are possible.In addition, any reference mark in claims should be configured to limit scope of the present utility model.
Claims (23)
1. Sealing, it is arranged between the entrance end of the outlet end of firing chamber and turbine nozzle, it is characterized in that, described Sealing is made by flexible exotic material, it comprises the first hermetic unit at least, the second hermetic unit and the 3rd hermetic unit, wherein, described the second hermetic unit radially is arranged in the outside of described the first hermetic unit, relatively described the first hermetic unit of described the 3rd hermetic unit and described the second hermetic unit are axially arranged, one of them of the outlet end of described the first hermetic unit and described the second hermetic unit and described firing chamber and the entrance end of described turbine nozzle connects, and another of the entrance end of the outlet end of described the 3rd hermetic unit and described firing chamber and described turbine nozzle connects.
2. Sealing according to claim 1, it is characterized in that, one of them of the outlet end of described the first hermetic unit and described the second hermetic unit and described firing chamber and the entrance end of described turbine nozzle connects in the mode that face contacts, and another of the outlet end of described the 3rd hermetic unit and described firing chamber and the entrance end of described turbine nozzle connects in the mode that face contacts.
3. Sealing according to claim 1 is characterized in that, described the first hermetic unit and described the second hermetic unit are mutually symmetrical.
4. Sealing according to claim 1 is characterized in that, the outer surface of described the first hermetic unit, described the second hermetic unit and/or described the 3rd hermetic unit is curved.
5. Sealing according to claim 1 is characterized in that, described Sealing is annular.
6. Sealing according to claim 1 is characterized in that, described Sealing is arc.
7. Sealing according to claim 1 is characterized in that, described Sealing also is limited with the cooling impact opening, so that the gas outside the described firing chamber cools off described Sealing through described cooling impact opening.
8. Sealing according to claim 1 is characterized in that, has wear resistant coating on the surface of at least one of described the first hermetic unit, the second hermetic unit and the 3rd hermetic unit.
9. Sealing according to claim 8 is characterized in that, described wear resistant coating is formed by the nickel-base material alloy.
10. Sealing, it is arranged in the gap that is jointly limited by firing chamber and turbine nozzle in order to sealing to be provided, described firing chamber provides the first sealing surfaces, described turbine nozzle provides the second sealing surfaces, it is characterized in that, described Sealing is made by flexible exotic material, it comprises the first hermetic unit, the second hermetic unit, the 3rd hermetic unit and the 4th hermetic unit, wherein, described the first hermetic unit and described the 3rd hermetic unit are axially arranged symmetrically, described the second hermetic unit and described the 4th hermetic unit are axially arranged symmetrically, described the second hermetic unit radially is arranged in the outside of described the first hermetic unit, and described the 4th hermetic unit radially is arranged in the outside of described the 3rd hermetic unit; Wherein, one of them of described the first hermetic unit and described the second hermetic unit and described the first sealing surfaces and described the second sealing surfaces connects, and another of described the 3rd hermetic unit and described the 4th hermetic unit and described the first sealing surfaces and described the second sealing surfaces connects.
11. Sealing according to claim 10, it is characterized in that, described the first hermetic unit connects in the mode that face contacts with one of them with described the first sealing surfaces and described the second sealing surfaces of described the second hermetic unit, and another of described the 3rd hermetic unit and described the 4th hermetic unit and described the first sealing surfaces and described the second sealing surfaces connects in the mode that face contacts.
12. Sealing according to claim 10 is characterized in that, described the first hermetic unit and described the second hermetic unit are symmetrical, and described the 3rd hermetic unit and described the 4th hermetic unit are symmetrical.
13. Sealing according to claim 12 is characterized in that, described the first hermetic unit and described the 3rd hermetic unit are symmetrical, and described the second hermetic unit and described the 4th hermetic unit are symmetrical.
14. each described Sealing is characterized in that according to claim 10-13, described the first hermetic unit and described the 3rd hermetic unit form the inside roughly V-arrangement of opening or C shape roughly.
15. each described Sealing is characterized in that according to claim 10-13, described the second hermetic unit and described the 4th hermetic unit form the roughly V-arrangement of outward opening or C shape roughly.
16. each described Sealing is characterized in that according to claim 10-13, described Sealing roughly is the figure of eight or " X " font.
17. Sealing according to claim 10 is characterized in that, described the first hermetic unit and described the second hermetic unit partly are connected to described the 3rd hermetic unit and the 4th hermetic unit by intermediate seal.
18. Sealing according to claim 17 is characterized in that, described intermediate seal part undulate.
19. Sealing according to claim 17 is characterized in that, described intermediate seal part roughly is O shape, U-shaped, V-arrangement, M shape or W shape.
20. Sealing according to claim 10 is characterized in that, described Sealing is annular.
21. Sealing according to claim 10 is characterized in that, described Sealing is arc.
22. Sealing according to claim 10 is characterized in that, described Sealing also is limited with the cooling impact opening, so that the gas outside the described firing chamber cools off described Sealing through described cooling impact opening.
23. Sealing, it is arranged in the gap that is jointly limited by firing chamber and turbine nozzle in order to sealing to be provided, described firing chamber provides the first sealing surfaces, described turbine nozzle provides the second sealing surfaces, it is characterized in that, described Sealing is made by flexible exotic material, it comprises that at least first surface contact hermetic unit contacts hermetic unit with second, wherein, described first surface contact hermetic unit is used for inner ground and face seals described the first sealing surfaces and described the second sealing surfaces contiguously, and described second contact hermetic unit is used for outer ground and face seals described the first sealing surfaces and described the second sealing surfaces contiguously.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220349162 CN202811083U (en) | 2012-07-18 | 2012-07-18 | Sealing element |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220349162 CN202811083U (en) | 2012-07-18 | 2012-07-18 | Sealing element |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202811083U true CN202811083U (en) | 2013-03-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220349162 Expired - Lifetime CN202811083U (en) | 2012-07-18 | 2012-07-18 | Sealing element |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202811083U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103573416B (en) * | 2012-07-18 | 2017-02-15 | 中航商用航空发动机有限责任公司 | Sealing member |
| CN111279103A (en) * | 2017-10-26 | 2020-06-12 | 赛峰短舱公司 | Propulsion unit for an aircraft |
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2012
- 2012-07-18 CN CN 201220349162 patent/CN202811083U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103573416B (en) * | 2012-07-18 | 2017-02-15 | 中航商用航空发动机有限责任公司 | Sealing member |
| CN111279103A (en) * | 2017-10-26 | 2020-06-12 | 赛峰短舱公司 | Propulsion unit for an aircraft |
| CN111279103B (en) * | 2017-10-26 | 2022-01-07 | 赛峰短舱公司 | Propulsion unit for an aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 201109 Shanghai city Minhang District Hongmei Road No. 5696 Room 101 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
|
| CP03 | Change of name, title or address |