CN111764969B - Aeroengine sealing structure - Google Patents
Aeroengine sealing structure Download PDFInfo
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- CN111764969B CN111764969B CN202010734253.7A CN202010734253A CN111764969B CN 111764969 B CN111764969 B CN 111764969B CN 202010734253 A CN202010734253 A CN 202010734253A CN 111764969 B CN111764969 B CN 111764969B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
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- General Engineering & Computer Science (AREA)
- Sealing Using Fluids, Sealing Without Contact, And Removal Of Oil (AREA)
Abstract
The application belongs to aeroengine structural design field, in particular to aeroengine structure of obturaging includes: the grate bushing is coaxially embedded on the inner ring surface of the high-speed shaft; the grate is coaxially arranged on the outer ring surface of the low-speed shaft through a deformable support piece, the arrangement position of the grate is matched with the grate lining, and in addition, the deformable support piece can drive the grate to be gradually far away from the axis of the low-speed shaft along the radial direction in the process of gradually increasing the rotating speed of the low-speed shaft. The sealing structure of the aero-engine can prevent the labyrinth gap from increasing in the operation process of the engine and keep the labyrinth sealing effect; in addition, the elastic compensation function can enable the labyrinth to have good sealing effect under different engine states, guarantee is provided for the realization of the functions of an air system, and guarantee is provided for the safe operation of the engine.
Description
Technical Field
The application belongs to the field of aero-engine structural design, and particularly relates to an aero-engine sealing structure.
Background
In aircraft engines, sealing between rotating and stationary components (rotary-stationary) and between rotating and rotating components (rotary-rotary) is usually performed by means of a labyrinth structure. Wherein, the obturating effect of the labyrinth plays a key role in realizing the functions of adjusting the axial force of the rotor of the air system, obturating the wheel rim and the like. And the sealing clearance is one of the most critical parameters influencing the sealing characteristic of the labyrinth, the larger the sealing clearance is, the poorer the sealing effect of the labyrinth is, and otherwise, the better the sealing effect is.
In the double-rotor aircraft engine, the high-pressure and low-pressure rotors are sealed by adopting a rotary-rotary type comb tooth seal. In the process of high-speed operation of the engine, due to the effect of centrifugal force, the grate bushing can displace to a high-radius position, so that the sealing clearance of the grate is increased, the sealing effect of the grate is weakened, the realization of the function of an air system of the engine is influenced, and hidden danger is brought to the safe operation of the engine.
Disclosure of Invention
In order to solve at least one of the technical problems, the application provides a sealing structure of an aircraft engine.
The application discloses aeroengine structure of obturating includes:
the grate bushing is coaxially embedded on the inner ring surface of the high-speed shaft;
the grid teeth are coaxially arranged on the outer ring surface of the low-speed shaft through a deformable support piece, the arrangement position of the grid teeth is matched with that of the grid teeth lining, and in addition, the deformable support piece can drive the grid teeth to be gradually far away from the axis of the low-speed shaft along the radial direction in the process that the rotating speed of the low-speed shaft is gradually increased.
According to at least one embodiment of the present application, the deformable support comprises:
the first support part is annular, and one end of the inner ring of the first support part is coaxially connected with the low-speed shaft;
the deformation part is cylindrical, and one axial end of the deformation part is coaxially connected with one end of the outer ring of the first support part;
the cylindrical second supporting part is coaxially connected with one axial end of the deformation part, and the outer ring surface of the second supporting part is provided with the comb teeth; wherein
The first supporting part is used for supporting the deformation part and the second supporting part, and the deformation part is used for driving the second supporting part and the comb teeth arranged on the second supporting part to move in the deformation process.
According to at least one embodiment of the present application, in the first support portion, the deformation portion, and the second support portion:
the first supporting part extends for a certain distance along the radial direction of the high-speed shaft and then is connected with one end, close to the first supporting part, of the deformation part;
the radial distance from one end of the deformation part close to the first support part to the low-speed shaft is smaller than the radial distance from one end of the deformation part far away from the first support part to the low-speed shaft;
the second support portion is connected to an end of the deformation portion, which is far away from the first support portion, and extends toward an end of the deformation portion, which is close to the first support portion, along an axial direction of the high-speed shaft.
According to at least one embodiment of the application, the connection position of the first supporting part and the deformation part adopts circular arc transition connection.
According to at least one embodiment of the present application, the connection between the deformation portion and the second support portion is an arc transition connection.
According to at least one embodiment of the present application, the first support portion has a uniform thickness in the axial direction of the high speed shaft.
According to at least one embodiment of the present application, the thickness gradually decreases from an end of the deformation portion close to the first support portion to an end thereof far from the first support portion.
According to at least one embodiment of the present application, the first supporting portion, the deformation portion, the second supporting portion, and the comb teeth are integrally formed members.
The application has at least the following beneficial technical effects:
the sealing structure of the aero-engine can prevent the labyrinth gap from increasing in the operation process of the engine and keep the labyrinth sealing effect; in addition, the elastic compensation function can enable the labyrinth to have good sealing effect under different engine states, guarantee is provided for the realization of the functions of an air system, and guarantee is provided for the safe operation of the engine.
Drawings
FIG. 1 is a structural cross-sectional view of an aircraft engine seal structure according to the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the accompanying drawings are illustrative and intended to explain the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
It should be understood that technical terms such as "central", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., which may be referred to in the description of the present application, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the scope of the present application.
The aeroengine sealing structure of the present application is further described in detail below with reference to fig. 1.
The application discloses aeroengine structure of obturating can include labyrinth bush 1 and labyrinth 3).
Specifically, the grate bush 1 is coaxially embedded on the inner ring surface of the high-speed shaft 2; the comb teeth 3 are coaxially arranged on the outer ring surface of the low-speed shaft 4 through a deformable support piece, the arrangement position of the comb teeth is matched with that of the comb teeth bush 1, in addition, the deformable support piece can drive the comb teeth 3 to be gradually far away from the axis of the low-speed shaft 4 along the radial direction in the process that the rotating speed of the low-speed shaft 4 is gradually increased, and elastic compensation is realized; it can be understood that when the rotation speed of the low-speed shaft 4 is gradually reduced, the deformable support can drive the grid teeth 3 to gradually approach the axial center of the low-speed shaft 4 along the radial direction.
It should be further explained that the principle of elastic compensation of the aeroengine sealing structure of the present application is as follows:
when the engine runs at a high speed, the radial position of the grate liner 1 is high, the rotating speed is high, the offset to the high radial position is large, so that the grate gap is increased, and the grate tooth ring (formed by the grate 3 and the deformable support) with the elastic compensation function can move to the high radial position along with the grate liner 1 under the action of centrifugal force, so that the rotating-rotating type sealing grate gap is kept (namely the grate gap is kept unchanged), and the sealing effect of the grate is ensured.
In conclusion, the aero-engine sealing structure can prevent the labyrinth gap from increasing in the running process of the engine and keep the labyrinth sealing effect; in addition, the elastic compensation function can enable the labyrinth to have good sealing effect under different engine states, guarantee is provided for the realization of the functions of an air system, and guarantee is provided for the safe operation of the engine.
Further, the deformable support of the present application may be configured in a variety of suitable shape configurations as desired; in the present embodiment, as shown in fig. 1, the upper half of the cross section of the deformable support member is preferably approximately "Z" shaped or "2" shaped, wherein the deformable support member may include a first support portion 51, a deformation portion 52, and a second support portion 53.
Specifically, the first support part 51 is annular, and one end of the inner ring (i.e., the end where the inner ring surface is located) is coaxially connected to the low-speed shaft 4; the deformation portion 52 is cylindrical, and one axial end (left end in fig. 1) thereof is coaxially connected to one end (i.e., the end of the outer ring surface) of the outer ring of the first support portion 51; the second support portion 53 is cylindrical, one axial end (right end in fig. 1) thereof is coaxially connected to the other axial end (right end in fig. 1) of the deformation portion 52, and the outer circumferential surface of the second support portion 53 is provided with the labyrinth 3.
Wherein, the first supporting portion 51 mainly plays a supporting role for supporting the deformation portion 52 and the second supporting portion 53; the deformation part 52 is used for realizing elastic deformation and driving the second support part 53 and the comb teeth 3 arranged on the second support part to move in the deformation process.
Further, among the first support portion 51, the deformable portion 52, and the second support portion 53, the first support portion 51 is extended a distance in the radial direction of the high-speed shaft 2, and then connected to one end (left end in fig. 1) of the deformable portion 52 near the first support portion 51; in addition, the radial distance from one end (left end in fig. 1) of the deformation portion 52 close to the first support portion 51 to the low-speed shaft 4 is smaller than the radial distance from one end (right end in fig. 1) of the deformation portion 52 far from the first support portion 51 to the low-speed shaft 4, that is, the deformation portion 52 is approximately in a bell mouth shape, and the radius of the left end is smaller than that of the right end; further, the second support portion 53 is connected to one end (right end in fig. 1) of the deformable portion 52, which is far from the first support portion 51, and then extends toward one end of the deformable portion 52, which is close to the first support portion 51, along the axial direction of the high speed shaft 2.
Further, at the joint of the first support part 51, the deformation part 52 and the second support part 53, it is preferable that the joint of the first support part 51 and the deformation part 52 is in a circular arc transition connection, and it is preferable that the joint of the deformation part 52 and the second support part 53 is in a circular arc transition connection.
Further, the thickness of each of the positions of the first support portion 51, the deformation portion 52, and the second support portion 53 may be set as appropriate as needed, and in the present embodiment, it is preferable that the thickness of the first support portion 51 is uniform in the axial direction of the high speed shaft 2 (i.e., in the left-to-right direction or right-to-left direction in fig. 1); and, the thickness gradually decreases from the end of the deformation portion 52 close to the first support portion 51 to the end thereof far from the first support portion 51.
In addition, the first support part 51, the deformation part 52, the second support part 53 and the comb 3 may be connected by various suitable connection methods, such as welding and bonding, and in the present embodiment, the first support part 51, the deformation part 52, the second support part 53 and the comb 3 are preferably integrally formed, so that the structural stability is enhanced. In addition, in other embodiments, even the low speed shaft 4 may be an integrally formed member with the above components, as the machining conditions permit.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. An aeroengine structure that obturages, its characterized in that includes:
the grate liner (1) is coaxially embedded in the inner annular surface of the high-speed shaft (2);
the comb teeth (3) are coaxially arranged on the outer ring surface of the low-speed shaft (4) through a deformable support piece, the arrangement position of the comb teeth (3) is matched with that of the comb teeth bush (1), and in addition, the deformable support piece can drive the comb teeth (3) to gradually get away from the axis of the low-speed shaft (4) along the radial direction in the process that the rotating speed of the low-speed shaft (4) is gradually increased;
the deformable support comprises:
the low-speed shaft bearing comprises a first annular supporting part (51), wherein one end of the inner ring of the first supporting part (51) is coaxially connected with the low-speed shaft (4);
a cylindrical deformation portion (52), wherein one axial end of the deformation portion (52) is coaxially connected with one end of the outer ring of the first support portion (51);
a cylindrical second support part (53), wherein one axial end of the second support part (53) is coaxially connected with the other axial end of the deformation part (52), and the outer annular surface of the second support part (53) is provided with the grid teeth (3); wherein
The first supporting part (51) is used for supporting the deformation part (52) and the second supporting part (53), and the deformation part (52) is used for driving the second supporting part (53) and the comb teeth (3) arranged on the second supporting part to move in the deformation process;
the thickness gradually decreases from one end of the deformation portion (52) close to the first support portion (51) to one end thereof far from the first support portion (51).
2. The aeroengine sealing structure according to claim 1, wherein, in the first support portion (51), deformation portion (52), and second support portion (53):
the first supporting part (51) extends for a distance along the radial direction of the high-speed shaft (2) and then is connected with one end, close to the first supporting part (51), of the deformation part (52);
the radial distance from one end of the deformation part (52) close to the first support part (51) to the low-speed shaft (4) is smaller than the radial distance from one end of the deformation part far away from the first support part (51) to the low-speed shaft (4);
the second support part (53) is connected with one end of the deformation part (52) far away from the first support part (51), and then extends towards one end of the deformation part (52) close to the first support part (51) along the axial direction of the high-speed shaft (2).
3. The aircraft engine sealing structure according to claim 2, wherein the junction of the first supporting portion (51) and the deformation portion (52) adopts an arc transition connection.
4. The aeroengine sealing structure according to claim 2, wherein the junction of the deformation portion (52) and the second support portion (53) is in a circular arc transition connection.
5. The aeroengine sealing structure according to claim 2, wherein the thickness of the first support portion (51) is uniform in the axial direction of the high-speed shaft (2).
6. The aircraft engine sealing structure according to claim 5, wherein the first supporting part (51), the deformation part (52), the second supporting part (53) and the labyrinth (3) are integrally formed components.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010734253.7A CN111764969B (en) | 2020-07-27 | 2020-07-27 | Aeroengine sealing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010734253.7A CN111764969B (en) | 2020-07-27 | 2020-07-27 | Aeroengine sealing structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111764969A CN111764969A (en) | 2020-10-13 |
| CN111764969B true CN111764969B (en) | 2022-08-30 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010734253.7A Active CN111764969B (en) | 2020-07-27 | 2020-07-27 | Aeroengine sealing structure |
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| Country | Link |
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| CN (1) | CN111764969B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1242787A (en) * | 1968-06-05 | 1971-08-11 | United Aircraft Corp | Seal construction |
| EP0340883A1 (en) * | 1988-05-06 | 1989-11-08 | General Electric Company | High pressure seal |
| CN106761956A (en) * | 2017-02-21 | 2017-05-31 | 北京航空航天大学 | It is a kind of to turn quiet system's encapsulating method using the aero-engine being axially combined with radial direction comb tooth |
| CN107269396A (en) * | 2017-08-17 | 2017-10-20 | 中国科学院工程热物理研究所 | A kind of achievable bearing seal structure that chamber and bearing exocoel are pressed altogether |
| CN109505665A (en) * | 2018-12-26 | 2019-03-22 | 北京航空航天大学 | A kind of densification device based on aero-engine seal pan axial force negative feedback control |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6547522B2 (en) * | 2001-06-18 | 2003-04-15 | General Electric Company | Spring-backed abradable seal for turbomachinery |
| US6619908B2 (en) * | 2001-09-10 | 2003-09-16 | Pratt & Whitney Canada Corp. | Axial and radial seal arrangement |
| US9181817B2 (en) * | 2010-06-30 | 2015-11-10 | General Electric Company | Method and apparatus for labyrinth seal packing rings |
| US20130287551A1 (en) * | 2012-04-27 | 2013-10-31 | General Electric Company | Separable seal assembly for a gas turbine engine |
| US10774668B2 (en) * | 2017-09-20 | 2020-09-15 | General Electric Company | Intersage seal assembly for counter rotating turbine |
-
2020
- 2020-07-27 CN CN202010734253.7A patent/CN111764969B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1242787A (en) * | 1968-06-05 | 1971-08-11 | United Aircraft Corp | Seal construction |
| EP0340883A1 (en) * | 1988-05-06 | 1989-11-08 | General Electric Company | High pressure seal |
| CN106761956A (en) * | 2017-02-21 | 2017-05-31 | 北京航空航天大学 | It is a kind of to turn quiet system's encapsulating method using the aero-engine being axially combined with radial direction comb tooth |
| CN107269396A (en) * | 2017-08-17 | 2017-10-20 | 中国科学院工程热物理研究所 | A kind of achievable bearing seal structure that chamber and bearing exocoel are pressed altogether |
| CN109505665A (en) * | 2018-12-26 | 2019-03-22 | 北京航空航天大学 | A kind of densification device based on aero-engine seal pan axial force negative feedback control |
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| Publication number | Publication date |
|---|---|
| CN111764969A (en) | 2020-10-13 |
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