CN204226022U - Face seal components and gas turbine engine - Google Patents
Face seal components and gas turbine engine Download PDFInfo
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- CN204226022U CN204226022U CN201420677653.9U CN201420677653U CN204226022U CN 204226022 U CN204226022 U CN 204226022U CN 201420677653 U CN201420677653 U CN 201420677653U CN 204226022 U CN204226022 U CN 204226022U
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- rotating ring
- face seal
- seal components
- lubricating oil
- passage
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Abstract
The purpose of this utility model is to provide a kind of face seal components and gas turbine engine, and the cooling effect of its cooling structure is more efficient.For realizing the face seal components of described object, comprise for being fixedly mounted on rotating ring in rotating shaft and for being arranged on the stationary ring on stationary holder, between rotating ring and stationary ring, end contact forms seal interface, be characterized in, rotating ring has main cooling section and between rotating ring inner circumferential side energy and described rotating shaft, forms the lubricating oil approach section of the annular of passage, lubricating oil approach section and main cooling section connected directly or indirectly, main cooling section has the oil pathway extended with overall non-linear outside the inside of rotating ring inner peripheral portion to rotating ring peripheral part.
Description
Technical field
The utility model relates to face seal components and comprises the gas turbine engine of this face seal components, particularly relates to the cooling structure of this face seal components.
Background technique
In gas turbine engine, seal the performance to product, reliability, life-span and maintainability and there is significant impact.In current gas turbine engine, one of widely used seal form is end face seal, as depicted in figs. 1 and 2, it is made up of sealing change 100, static components 103, auxiliary seal ring 101, bracket 102, stop pin 105 and elastic element 104 usually, and sealing change 100 is fastened on axle by locking nut 106.Between sealing change 100, static components 103, two coating surfaces and auxiliary seal ring 101 limit the leakage of gas in relative rotation.Operationally, the surface that sealing change 100 and static components 103 fit relatively rotates, and constitutes rubbing surface, produces amount of heat.These caloric requirements distribute, otherwise can produce disadvantageous thermal distortion, cause sealing wear to aggravate, reduction of service life.Above-mentioned this situation change 100 and static components 103 relative rotation speed larger time, can especially seriously, and the requirement of advanced gas turbine engines to rotating speed be more and more higher, be sealed into one of factor that row cooling becomes its application of restriction efficiently to end face.
At present, the type of cooling of end face seal has two kinds, as depicted in figs. 1 and 2.Fig. 1 is inner-cooled structure, and lubricating oil flows through the passage of sealing change 100 inside, throws away under the influence of centrifugal force, takes away heat and cool.What extensively adopt now is this form, and the oil through 107 shown in Fig. 1 limits the area of contact of lubricating oil and change 100, and the heat that lubricating oil is taken away is limited.Figure 2 shows that external-cooling type structure, utilize lubricating oil nozzle 108 to carry out impinging cooling to sealing change 100 outer surface, its structure is simple, is easy to realize, but cooling effect is not good.
Model utility content
The purpose of this utility model is to provide a kind of face seal components, and the cooling effect of its cooling structure is more efficient.
Another object of the present utility model is to provide a kind of gas turbine engine containing this face seal components.
For realizing the face seal components of described object, comprise for being fixedly mounted on rotating ring in rotating shaft and for being arranged on the stationary ring on stationary holder, between rotating ring and stationary ring, end contact forms seal interface, be characterized in, rotating ring has main cooling section and between rotating ring inner circumferential side energy and described rotating shaft, forms the lubricating oil approach section of the annular of passage, lubricating oil approach section and main cooling section connected directly or indirectly, main cooling section has the oil pathway extended with overall non-linear outside the inside of rotating ring inner peripheral portion to rotating ring peripheral part.
Described face seal components, its further feature is, main cooling section also has the annular pass formed in rotating ring inner peripheral portion inside, and multiple described oil pathway along the circle distribution of rotating ring, and stretches out from annular pass and runs through rotating ring.
Described face seal components, its further feature is, described oil pathway is Y-shaped structure.
Described face seal components, its further feature is, described oil pathway comprises first passage, second channel and third channel, first passage extends out to rotating ring periphery from described annular pass and runs through rotating ring, second channel extends out to rotating ring periphery from first passage and runs through rotating ring, and third channel extends out to rotating ring periphery from second channel and runs through rotating ring.
Described face seal components, its further feature is, the sense of rotation of the relative rotating ring of each passage tilts backwards.
Described face seal components, its further feature is that main cooling section is connected with lubricating oil approach section by changeover portion, changeover portion be rotating ring axially extend and with rotating ring axis in an angle.
Described face seal components, its further feature is, described oil pathway is arc.
Described face seal components, its further feature is, described oil pathway is in the inner spirality along rotating ring circumferencial direction spiral extension of rotating ring.
Described face seal components, its further feature is, described rotating ring is by increasing manufacture process manufacture.
For realizing the gas turbine engine of described object, comprise the axle by bearings, bearing is installed on the stationary holder of motor, and be arranged in a bearing bore, seal between axle and stationary holder to make bearing bore be a confined space, be sealed into end face seal described at least one place, it is characterized in that, it is aforesaid face seal components that described end face seal place is arranged.
Because main cooling section has the oil pathway extended with overall non-linear outside the inside of rotating ring inner peripheral portion to rotating ring peripheral part, the area of contact limited with runway compared to the lubricating oil of at present conventional internal cooling end face sealing, the utility model can obtain the Maximum Contact area of lubricant oil under intensity permission and rotating ring; In addition, owing to being the oil pathway that non-linear extends, and the utility model can when meeting requirement of strength, the distance of cooling channel and rubbing surface is made to reach minimum, larger area of contact and the shorter distance to rubbing surface, lubricating oil can be allowed to take away more frictional heat, thus reach better cooling effect.
Accompanying drawing explanation
The above and other feature of the present utility model, character and advantage become more obvious by passing through below in conjunction with the description of drawings and Examples, wherein:
Fig. 1 is the schematic diagram of the structure of existing face seal components.
Fig. 2 is the schematic diagram of the another kind of structure of existing face seal components.
Fig. 3 is the structure diagram of gas turbine engine.
Fig. 4 is a partial view of gas turbine engine.
Fig. 5 is the structural representation of the rotating ring (runway) in the sealing of a kind of internal cooling end face.
Fig. 6 is the cross section view along the rotating ring (runway) of Fig. 7 center line B-O-B in the utility model embodiment.
Fig. 7 is the cross section view along A-A line in Fig. 6.
Fig. 8 is the three-dimensional view of the rotating ring (runway) after clipping the part in Fig. 6 in dotted line frame.
Fig. 9 is the cross section view of A-A line position in the roughly corresponding diagram 6 of rotating ring in another embodiment of the utility model.
Figure 10 is the cross section view of A-A line position in the roughly corresponding diagram 6 of rotating ring in the another embodiment of the utility model.
Embodiment
Below in conjunction with specific embodiments and the drawings, the utility model is described in further detail; set forth more details in the following description so that fully understand the utility model; but the utility model obviously can be implemented with multiple this alternate manner described that is different from; those skilled in the art when doing similar popularization, deduction without prejudice to when the utility model intension according to practical situations, therefore can should not limit protection domain of the present utility model with the content of this specific embodiment.
In the following description, with reference to each embodiment, the utility model is described.But, person of skill in the art will appreciate that and can replace when neither one or multiple specific detail or with other and/or implement each embodiment together with addition method, material or assembly.In other situation, not shown or do not describe known structure, material or operation in detail in order to avoid make the aspects of each embodiment of the present utility model obscure.Similarly, in order to the object explained, specific quantity, material and configuration are set forth, to provide the complete understanding to embodiment of the present utility model.But the utility model can be implemented when not having specific detail.In addition, each embodiment shown in accompanying drawing should be understood be illustrative expression and not necessarily draw in proportion.
Fig. 3, Fig. 4, Fig. 6, Fig. 7 and Fig. 8 show an embodiment of the present utility model, and Fig. 9, Figure 10 show the different piece of two other embodiment.It should be noted that these and other accompanying drawing all only exemplarily, it is not draw according to the condition of equal proportion, and should not be construed as limiting in this, as to the protection domain of the utility model actual requirement.
In addition, the foregoing description of embodiment of the present utility model has been given for the purpose of illustration and description.Do not intend exhaustive or the utility model is limited to disclosed precise forms.This specification and claims comprise such as left and right, top, the end ... on ... under, top, bottom, first, second, the term such as inside and outside, radial, circumferential, axial, these only should not be construed as restriction for the object described.Such as, the axis indicating the term of relative radial direction or axis to refer to the axle of rotating ring or installation rotating ring is references object; Left and right is for reference with the situation shown in scheming.Those skilled in the relevant art can understand a lot of amendment according to above teaching and distortion is possible.Person of skill in the art will appreciate that various equivalent combinations and the replacement of each assembly shown in accompanying drawing.Therefore scope of the present utility model is not limited by this detail specifications but be defined by the following claims.
Figure 3 shows that an aeroengine structure diagram, it is connected on the same axis by the gas compressor 1 of rotation and turbine 3, thermal source is housed between the two---firing chamber 2, air is continuously inhaled into gas compressor 1, and after compressing supercharging wherein, enter oil jetting combustion in firing chamber 2 and become high-temperature high-pressure fuel gas, enter expansion work in turbine 3 again, a part of expansion work passes to gas compressor by transmission shaft, in order to pressurized air, another part then externally exports, as the power of aircraft.
Figure 4 shows that a Local map of aeroengine shown in Fig. 3.Hollow shaft 4 is by bearings on the static element of motor, and one of them bearing is illustrated bearing 5, and bearing 5 is installed on stationary holder 6, and bearing 5 is arranged in bearing bore 8, and bearing bore 8 is the chambers surrounded by stationary holder 6, stationary holder 7 and axle 4.The major function of bearing bore 8 transmits radial force and the axial force of engine rotor, provides a space held for the lubricating oil of element in lubrication bearing bore.Canned rotor part 9 is installed on axle 4, forms sealing together with stationary holder 7, reduces or stops lubricating oil to leak to chamber from the right-hand member of bearing bore 8.Sealing 10 reduces or stops lubricating oil to leak to chamber from the left end of bearing bore 8.
In embodiment of the present utility model, Sealing 10 is face seal components, and black box 10 comprises stationary ring 10a and rotating ring 10b.Stationary ring 10a is installed on stationary holder 06, and rotating ring (also claim " runway) 10b is installed on axle 4.The end face 10aa of stationary ring 10a contacts with the end face 10bb of rotating ring 10b, constitutes seal interface.When end face seal works, rotating ring 10b relative stationary ring 10a High Rotation Speed, the end face 10aa fitted and end face 10bb rubs and produces amount of heat, and these caloric requirements shed, otherwise can produce disadvantageous thermal distortion, cause the heavy wear of end face seal.
Oil system provides the friction element of the lubricating oil with certain pressure for lubricating and in cooling bearing chamber, as bearing 5 and end face seal 10.Lubricating oil is by after the supercharging of lubricating oil pump (not shown), and the nozzle 13 through fuel supply line 12 sprays.Fuel supply line 12 is installed on stationary holder 6.Nozzle 13 has certain angle, and guiding lubricating oil enters the path 10 bc on rotating ring 10b.Before lubricating oil inlet passage 10bc, lubricating oil first have passed through the passage 15a on the locking nut 15 and passage 5a in bearing 5 inner ring.Arrive the lubricating oil of path 10 bc, under the influence of centrifugal force, via path 10 bd and path 10 be, get rid of in bearing bore 08, take away the heat that seal interface produces, thus reach cooling effect.
Fig. 5 is the rotating ring 11 in the sealing of a kind of internal cooling end face, and its its right end face 11a is rubbing surface.Inner cylindrical surface 11b matches with axle 4, and axle 4 and inner cylindrical surface 11c form passage 11d, and through hole 11e communicates with passage 11d, and rotating ring 11 is uniform some through hole 11e circumferentially.Lubricating oil enters from passage 11d, then under the influence of centrifugal force, throws away from through hole 11e.By contacting of the wall of lubricating oil and passage 11d and through hole 11e, take away a part of frictional heat that end face 11a produces.Embodiment of the present utility model described later and this oil pathway are in other words compared with cooling structure, and composition graphs and explanatory note are appreciated that, its cooling effect is more efficient.
Fig. 6 is the sectional view of the rotating ring 10b in the utility model one embodiment.Its its right end face 10bf is rubbing surface.In embodiment of the present utility model, the cooling structure being undertaken cooling by lubricant oil is three parts: lubricating oil approach section, as path 10 bc described later; Main cooling section, as oil pathway 10be described later; Changeover portion, path 10 bd described above.
In the embodiment shown in the drawings, inner cylindrical surface 10bg coordinates with axle 4, and axle 4 and inner cylindrical surface 10bh form path 10 bc.
Fig. 7 is the A-A sectional drawing of Fig. 6, shows the structure of oil pathway 10be.Oil pathway 10be comprises path 10 be1 (annular pass), path 10 be2 (first passage), path 10 be3 (second channel) and path 10 be4 (third channel).Path 10 be1 is ring.Path 10 be2, path 10 be3 and path 10 be4 are the curved channels extended to outer peripheral side from inner circumferential side, and entirety is Y-shaped.Wherein path 10 be2 connecting passage 10be1 and bearing bore 8, path 10 be3 connecting passage 10be2 and bearing bore 8, path 10 be4 connecting passage 10be3 and bearing bore 8, path 10 be2,10be3,10be4 are relative to the sense of rotation of rotating ring, be all tilted rearward, be convenient to like this by centrifugal force, lubricant oil be thrown away.Rotating ring 10b is uniform some such path 10 be along the circumferential direction.
For showing rotating ring 10b inner passage and lubricating oil mobility status better, the material in the dotted line interface of excision shown in Fig. 6, obtains structure shown in Fig. 8.Composition graphs 6 and Fig. 8, rotating ring 10b has path 10 bc, path 10 bd and path 10 be and forms, and path 10 bd is the some axial direct groove compositions be uniformly distributed circumferentially, and the center line of this direct through groove and the axis of axle 4 have a certain degree.Lubricating oil enters rotating ring 10b from path 10 bc, under the influence of centrifugal force, lubricating oil flows through path 10 bd, path 10 be1, path 10 be2, path 10 be3 and path 10 be4 successively, finally throws away from the jointing of path 10 be2, path 10 be3 and path 10 be4 and bearing bore 08.
The mode that the cooling channel of the complexity of Fig. 6 ~ Fig. 8 display can be, but not limited to by increasing manufacture process or 3D printing technique or Rapid Prototyping technique realizes.
Compared with the comparative example shown in Fig. 5, the oil pathway of the embodiment shown in Fig. 6 to Fig. 8 is longer, and therefore, the area of contact of lubricating oil and rotating ring 10b is larger, and lubricating oil can take away more heat, thus reaches better cooling effect.
Should be noted that, in the aforementioned embodiment, the structure of changeover portion (path 10 bd) is not limited only to the straight pass that above-mentioned axis is straight line, cross section is circle, and its axis and cross section can be arbitrary shapes, only need it to be communicated with main cooling section by lubricating oil approach section.Even, when structure and intensity allow, can save changeover portion, lubricating oil approach section one is also communicated with it immediately below main cooling section.
Should also be noted that main cooling section is not limited only to above-mentioned Y-shaped structure, its channel centerline can by arbitrary curve or rectilinear(-al), and its channel cross-section can also be arbitrary shape.
Fig. 9 and Figure 10 shows two other embodiment of the present utility model, these two embodiments continue to use element numbers and the partial content of previous embodiment, wherein adopt identical label to represent identical or approximate element, and optionally eliminate the explanation of constructed content.The profile position of Fig. 9 and Figure 10 display roughly corresponds to the profile position on the rotating ring shown in Fig. 6, and in these embodiments, the explanation about clipped can refer to previous embodiment, and it is no longer repeated for the present embodiment.
As shown in Figure 9, be provided with the main cooling section having and be uniformly distributed circumferentially some circular arc passages 16 in rotating ring 10b, with reference to figure 6, lubricating oil enters from path 10 bc, via path 10 bd or not via path 10 bd, finally throws away from passage 16.Passage 16 is circular arc, and compared to present linear passage 11e, circular arc passage is longer, so which provide the larger surface area that can contact with lubricating oil, when lubricating oil flows through, can take away more heat wherein, reach better cooling effect.
As shown in Figure 10, be provided with the main cooling section with spirality channel 17 in rotating ring 10b, its center line is a helix, and lubricating oil enters from path 10 bc, via path 10 bd or not via path 10 bd, finally throws away from passage 17.Similarly, relatively as shown in Figure 5, linear passage 11e, it can obtain larger lubricating oil contact surface area, and cooling effect is better.
Be appreciated that, main cooling section of the present utility model only needs it to be transported to bearing bore by lubricating oil from changeover portion or approach section, under the permission of intensity, main cooling section should be long as much as possible, the shape of its entirety is not limited to previous embodiment, is essentially non-linear, such as, can also be netted, large as much as possible to ensure the area of contact of lubricating oil and rotating ring, thus as often as possible take away heat.
Although the utility model with preferred embodiment openly as above, it is not that any those skilled in the art, not departing from spirit and scope of the present utility model, can make possible variation and amendment for limiting the utility model.Therefore, every content not departing from technical solutions of the utility model, any amendment done above embodiment according to technical spirit of the present utility model, equivalent variations and modification, all fall within protection domain that the utility model claim defines.
Claims (10)
1. face seal components, comprise for being fixedly mounted on rotating ring in rotating shaft and for being arranged on the stationary ring on stationary holder, between rotating ring and stationary ring, end contact forms seal interface, it is characterized in that, rotating ring has main cooling section and between rotating ring inner circumferential side energy and described rotating shaft, forms the lubricating oil approach section of the annular of passage, lubricating oil approach section and main cooling section connected directly or indirectly, main cooling section has the oil pathway extended with overall non-linear outside the inside of rotating ring inner peripheral portion to rotating ring peripheral part.
2. face seal components as claimed in claim 1, is characterized in that, main cooling section also has the annular pass formed in rotating ring inner peripheral portion inside, and multiple described oil pathway along the circle distribution of rotating ring, and stretches out from annular pass and runs through rotating ring.
3. face seal components as claimed in claim 2, it is characterized in that, described oil pathway is Y-shaped structure.
4. face seal components as claimed in claim 3, it is characterized in that, described oil pathway comprises first passage, second channel and third channel, first passage extends out to rotating ring periphery from described annular pass and runs through rotating ring, second channel extends out to rotating ring periphery from first passage and runs through rotating ring, and third channel extends out to rotating ring periphery from second channel and runs through rotating ring.
5. face seal components as claimed in claim 4, it is characterized in that, the sense of rotation of the relative rotating ring of each passage tilts backwards.
6. face seal components as claimed in claim 1, it is characterized in that, main cooling section is connected with lubricating oil approach section by changeover portion, changeover portion be rotating ring axially extension and with rotating ring axis in an angle.
7. face seal components as claimed in claim 1, it is characterized in that, described oil pathway is arc.
8. face seal components as claimed in claim 1, is characterized in that, described oil pathway is in the inner spirality along rotating ring circumferencial direction spiral extension of rotating ring.
9. face seal components as claimed in claim 1, it is characterized in that, described rotating ring is by increasing manufacture process manufacture.
10. a gas turbine engine, comprise the axle by bearings, bearing is installed on the stationary holder of motor, and be arranged in a bearing bore, seal between axle and stationary holder to make bearing bore be a confined space, be sealed into end face seal described at least one place, it is characterized in that, described end face seal place arranges face seal components as claimed in any one of claims 1-9 wherein.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420677653.9U CN204226022U (en) | 2014-11-13 | 2014-11-13 | Face seal components and gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420677653.9U CN204226022U (en) | 2014-11-13 | 2014-11-13 | Face seal components and gas turbine engine |
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| Publication Number | Publication Date |
|---|---|
| CN204226022U true CN204226022U (en) | 2015-03-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420677653.9U Active CN204226022U (en) | 2014-11-13 | 2014-11-13 | Face seal components and gas turbine engine |
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| CN (1) | CN204226022U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104942543A (en) * | 2015-06-15 | 2015-09-30 | 中国石油大学(华东) | Nanometer material increase manufacturing method of upstream pumping mechanical seal |
| CN105689796A (en) * | 2016-04-28 | 2016-06-22 | 山东理工大学 | Efficient saw head |
-
2014
- 2014-11-13 CN CN201420677653.9U patent/CN204226022U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104942543A (en) * | 2015-06-15 | 2015-09-30 | 中国石油大学(华东) | Nanometer material increase manufacturing method of upstream pumping mechanical seal |
| CN105689796A (en) * | 2016-04-28 | 2016-06-22 | 山东理工大学 | Efficient saw head |
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| Date | Code | Title | Description |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
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| CP01 | Change in the name or title of a patent holder |