CN109404546B - Sealing structure in engine mode selection mechanism and design method - Google Patents
Sealing structure in engine mode selection mechanism and design method Download PDFInfo
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- CN109404546B CN109404546B CN201811538288.2A CN201811538288A CN109404546B CN 109404546 B CN109404546 B CN 109404546B CN 201811538288 A CN201811538288 A CN 201811538288A CN 109404546 B CN109404546 B CN 109404546B
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- valve plate
- mode selection
- engine mode
- sealing
- valve
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K1/00—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces
- F16K1/16—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure-members
- F16K1/18—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure-members with pivoted discs or flaps
- F16K1/20—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure-members with pivoted discs or flaps with axis of rotation arranged externally of valve member
- F16K1/2014—Shaping of the valve member
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16K—VALVES; TAPS; COCKS; ACTUATING-FLOATS; DEVICES FOR VENTING OR AERATING
- F16K1/00—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces
- F16K1/16—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure-members
- F16K1/18—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure-members with pivoted discs or flaps
- F16K1/20—Lift valves or globe valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with pivoted closure-members with pivoted discs or flaps with axis of rotation arranged externally of valve member
- F16K1/2042—Special features or arrangements of the sealing
- F16K1/205—Special features or arrangements of the sealing the sealing being arranged on the valve member
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Check Valves (AREA)
- Lift Valve (AREA)
Abstract
The application belongs to the field of aircraft engine design, and particularly relates to a sealing structure and a design method in an engine mode selection mechanism, wherein the sealing structure provided by the application is used for solving the sealing problem in the aircraft engine mode selection mechanism, one end, close to a fan case, of a valve plate of the sealing structure provided by the application is arranged to enable the valve plate to keep a sealing surface with the fan case in the rotation process of the valve plate around an axis connecting line, a plurality of sealing sections at the port of the fan case are matched with the shape of the sealing surface of the valve plate, the sealing structure can keep sealing contact with the valve plate in the rotation process of the valve plate around the axis connecting line, and meanwhile, the continuity and the integrity of a flow.
Description
Technical Field
The application belongs to the field of aircraft engine design, and particularly relates to a sealing structure in an engine mode selection mechanism and a design method.
Background
The engine mode selection mechanism is a key adjusting mechanism component used for achieving adjustment of the internal and external air flow ratio in the variable-cycle aircraft engine. Structurally, the mode selection mechanism is typically located before the diverter ring, i.e., the bypass flow channel inlet, for opening or closing the bypass, thereby switching the engine between dual bypass and single bypass operating cycles. When the mode selection mechanism is in an open state, the mode selection mechanism needs to enable airflow to flow into the inner duct and the outer duct in a designed proportion without being blocked; when the valve is closed, the outer duct needs to be completely sealed, so that the airflow can completely flow into the inner duct. The difficulty is that no matter what state the mode selection mechanism is in, the function of adjusting the bypass ratio is realized, and meanwhile, the flow path is continuous, complete and good in sealing performance is kept, so that the pneumatic loss is reduced. In engineering application, because the mode selection valve is a rotary moving part and the geometry required by the mode selection valve is complex, how to design the mode selection valve to ensure that the mode selection valve can keep effective sealing at the rotating shaft of the valve plate in all states and simultaneously keep a flow path at the position complete and continuous is particularly difficult.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The sealing structure in the engine mode selection mechanism realizes the function of adjusting the bypass ratio, and simultaneously ensures that the flow path is continuous and complete and keeps good sealing performance.
The technical scheme of the application is as follows:
the present application provides, in a first aspect, a seal structure in an engine mode selection mechanism, the seal structure including:
the valve plates are circumferentially and uniformly arranged between the aircraft fan casing and the culvert runner inlet and can form a ring body matched with the fan casing, a first mounting plate and a second mounting plate are arranged on one surface of the valve plates, which is back to the interior of the ring body and is close to the fan casing, a first mounting hole is formed in the first mounting plate, a second mounting hole is formed in the second mounting plate, the axis connecting line of the first mounting hole and the second mounting hole is perpendicular to the central axis of the ring body, each valve plate can rotate around the axis connecting line, and one end, close to the fan casing, of each valve plate is arranged to enable the valve plate to keep a sealing surface with the fan casing in the rotating process of the valve plate around the axis connecting line;
the sealing sections are arranged at the port of the fan casing, are matched with the shapes of the sealing surfaces of the valve plates and can keep sealing contact with the valve plates in the process that the valve plates rotate around the axis connecting line.
According to at least one embodiment of the present application, the number of valve plates is at least 10.
According to at least one embodiment of the application, the position of two apex angles of the sealing surface of the valve plate is provided with a notch.
According to at least one embodiment of the present application, further comprising:
the rotating shaft is arranged in the first mounting hole and the second mounting hole;
the third mounting piece is arranged at a position, close to the culvert runner inlet, on one surface, back to the interior of the ring body, of the valve plate, and a third mounting hole is formed in the third mounting piece;
and the power mechanism is connected to the third mounting hole through a pin shaft and used for providing power to enable the valve plate to rotate around the rotating shaft.
According to at least one embodiment of the present application, further comprising:
the strengthening rib sets up on the valve block one side of the inside of ring body dorsad.
According to at least one embodiment of this application, the valve block still is provided with sealed recess towards on the terminal surface of the one end of culvert runner entry.
A second aspect of the present application provides a design method of a seal structure in an engine mode selection mechanism, the design method including the steps of:
step 3, rotating the edge for a certain angle around the axis connection line to form a sealing surface, and combining the arc-shaped surface with the sealing surface to form a valve sheet profile;
and 4, machining the end of the fan casing to form a contact surface matched with the sealing surface.
According to at least one embodiment of the present application, the line segment is rotated by an angle ≦ 36 degrees in step 1.
According to at least one embodiment of the application, the rotation angle of the edge in step 3 is determined according to the degree to which the valve plate needs to be opened.
According to at least one embodiment of the present application, step 4 further includes, after completion:
and processing the vertex angle position of the sealing surface, which is far away from the arc-shaped surface, and forming a notch at the vertex angle position.
The application has at least the following beneficial technical effects:
the application provides a valve block and engine fan machine casket port contact segment pass through contact edge rotational moulding, consequently can guarantee to keep contact seal at the valve block rotation in-process to can keep this complete smoothness of flow path simultaneously in effective sealing.
Drawings
FIG. 1 is a schematic structural view of a valve plate of the sealing structure of the present application;
FIG. 2 is a schematic view of the seal segment configuration of the seal configuration of the present application;
FIG. 3 is a schematic valve plate closing view of the seal of the present application;
fig. 4 is a valve plate opening schematic view of the sealing structure of the present application.
Wherein:
1-a fan case; 2, valve plates; 3-a first mounting hole; 4-a second mounting hole; 5-sealing surface; 6-sealing section; 7-a third mounting hole; 8-reinforcing ribs; 9-sealing the groove; 10-arc surface.
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 drawings are exemplary and intended to be used for explaining 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.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1 to 4.
The present application provides, in a first aspect, a seal structure in an engine mode selection mechanism, including a plurality of valve plates 2 and a plurality of seal segments 6.
Specifically, a plurality of valve plates 2 are circumferentially and uniformly arranged between an aircraft fan casing and a culvert runner inlet, a ring body matched with the fan casing 1 can be formed, the number of the valve plates 2 is at least 10, a first mounting plate and a second mounting plate are arranged on one surface, back to the interior of the ring body, of each valve plate 2, the surface, close to the fan casing is provided with a first mounting hole 3, a second mounting hole 4 is arranged on the first mounting plate, a shaft center connecting line c1 of each first mounting hole 3 and the corresponding second mounting hole 4 is perpendicular to the central axis of the ring body, each valve plate 2 can rotate around a shaft center connecting line c1, and one end, close to the fan casing 1, of each valve plate 2 is arranged to enable the valve plate 2 to keep a sealing surface 5 of the fan casing 1 in the rotating process of the valve plate 2 around the shaft center connecting line c 1.
And, the position of two apex angles of the sealed face 5 of valve block 2 is provided with the breach, prevents that two adjacent valve blocks 2 from interfering each other when being in the closed condition.
The sealing sections 6 are arranged at the port of the fan casing 1, are matched with the shapes of the sealing surfaces 5 of the valve plates 2, and can keep sealing contact with the valve plates 2 in the process that the valve plates 2 rotate around the axis connecting line c 1.
Further, the sealing structure in the engine mode selection mechanism of the application further comprises a rotating shaft, a third mounting piece and a power mechanism.
Specifically, the rotating shaft is installed in the first installation hole 3 and the second installation hole 4;
the third mounting piece is arranged at a position close to the culvert runner inlet on one surface of the valve plate 2, which is back to the interior of the ring body, and the third mounting piece is provided with a third mounting hole 7;
the power mechanism is connected to the third mounting hole 7 through a pin shaft and used for providing power to enable the valve plate 2 to rotate around the rotating shaft, and therefore opening and closing of the valve plate 2 are achieved.
Further, seal structure among this application engine mode selection mechanism still includes strengthening rib 8, and strengthening rib 8 sets up on the one side of valve block 2 inside the ring body dorsad for strengthen valve block 2's intensity.
Further, the valve block 2 still is provided with sealed recess 9 towards on the one end terminal surface of culvert runner entry, can make the valve block 2 be in closed condition can with the culvert runner entry between keep sealed, make the inlet flow path continuous, complete simultaneously.
A second aspect of the present application provides a design method of a seal structure in the engine mode selection mechanism, the design method including the steps of:
in addition, the rotation angle of the line segment A1 is less than or equal to 36 degrees, so that the sealing effect of the valve plates 2 can be ensured, and the influence between the adjacent valve plates 2 is reduced.
step 3, rotating the edge A2 for a certain angle around a shaft center connecting line c1 to form a sealing surface 5, combining the arc-shaped surface 10 with the sealing surface 5 to form a profile of the valve plate, determining the rotating angle of the edge A2 according to the required opening degree of the valve plate 2, and further processing the edge A2 into the valve plate 2;
and 4, machining the end of the fan casing 1 to form a shape matched with the sealing surface 5.
And after the step 4 is finished, the vertex angle position of the sealing surface 5 far away from the arc-shaped surface 10 is processed, and a notch is formed at the vertex angle position to prevent the two adjacent valve plates 2 from interfering with each other when being in a closed state.
After the sealing structure is processed, the valve plate 2 is assembled on the fan case 1 and can be assembled through the stay bar, one end of the stay bar is connected with the rotating shaft, and the other end of the stay bar is connected with the connecting part of the fan case 1.
This application can make valve block 2 keep sealed when being in the action, makes the inlet flow path continuous, complete simultaneously.
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 (10)
1. A seal structure in an engine mode selection mechanism, characterized by comprising:
the valve plates (2) are circumferentially and uniformly arranged between an aircraft fan casing and an outer culvert runner inlet, a ring body matched with the fan casing (1) can be formed, in addition, a first installation plate and a second installation plate are arranged at positions, close to the fan casing, of one face, back to the inside of the ring body, of the valve plates (2), a first installation hole (3) is formed in the first installation plate, a second installation hole (4) is formed in the second installation plate, an axle center connecting line (c1) of the first installation hole (3) and the second installation hole (4) is perpendicular to the central axis of the ring body, each valve plate (2) can rotate around the axle center connecting line (c1), each valve plate (2) comprises an arc-shaped surface (10) and a sealing surface (5) extending from the arc-shaped edge (A2) of the arc-shaped surface (10), wherein the sealing surface (5) is an axle center surface formed by rotating the connecting line (c1) by a certain angle for the edge (A2), the sealing surface (5) is butted on the fan casing (1);
the sealing sections (6) are arranged at the port of the fan casing (1), are matched with the sealing surfaces (5) of the valve plates (2) in shape, and can be in sealing contact with the valve plates (2) when the valve plates (2) rotate around the axis connecting line (c 1).
2. A seal structure in an engine mode select mechanism according to claim 1, characterized in that the number of the valve plate (2) is at least 10.
3. A seal structure in an engine mode selecting mechanism according to claim 1, characterized in that the positions of both top corners of the seal surface (5) of the valve sheet (2) are provided with notches.
4. The seal structure in the engine mode selection mechanism according to claim 1, characterized by further comprising:
the rotating shaft is arranged in the first mounting hole (3) and the second mounting hole (4);
the third mounting piece is arranged at a position, close to the culvert runner inlet, on one surface, back to the interior of the ring body, of the valve plate (2), and a third mounting hole (7) is formed in the third mounting piece;
and the power mechanism is connected to the third mounting hole (7) through a pin shaft and used for providing power to enable the valve plate (2) to rotate around the rotating shaft.
5. The seal structure in the engine mode selection mechanism according to claim 1, characterized by further comprising:
and the reinforcing rib (8) is arranged on one surface of the valve plate (2) back to the interior of the ring body.
6. The seal structure in the engine mode selection mechanism according to claim 1, characterized in that a seal groove (9) is further provided on an end surface of the valve plate (2) facing the inlet of the bypass flow passage.
7. A method of designing a seal structure in an engine mode selection mechanism, characterized by comprising the steps of:
step 1, rotating a line segment (A1) with a set length parallel to the central axis of a fan case (1) along the circumferential direction of the outer surface of the fan case (1) for a certain angle to form an arc-shaped surface (10), wherein one end trace of the line segment (A1) forms an arc-shaped edge (A2);
step 2, designing a first mounting piece and a second mounting piece on the arc-shaped surface (10), wherein the first mounting piece is provided with a first mounting hole (3), the second mounting piece is provided with a second mounting hole (4), and a shaft center connecting line (c1) of the first mounting hole (3) and the second mounting hole (4) is vertical to the central axis of the fan casing (1);
step 3, rotating the edge (A2) around the axis connecting line (c1) for a certain angle to form a sealing surface (5), combining the arc-shaped surface (10) with the sealing surface (5) to form a profile of the valve plate, and further processing the profile into the valve plate (2);
and 4, machining the end of the fan casing (1) to form a shape matched with the sealing surface (5).
8. The design method of a seal structure in an engine mode selection mechanism according to claim 7, characterized in that said line segment (A1) is rotated by an angle ≦ 36 degrees in step 1.
9. The design method of a seal structure in an engine mode selection mechanism according to claim 7, characterized in that the rotation angle of the rim (A2) in step 3 is determined according to the degree to which the valve sheet (2) needs to be opened.
10. The method of designing a seal structure in an engine mode selection mechanism according to claim 7, characterized in that step 4 is completed and further includes:
and processing the vertex angle position of the sealing surface (5) far away from the arc-shaped surface (10), and forming a notch at the vertex angle position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811538288.2A CN109404546B (en) | 2018-12-16 | 2018-12-16 | Sealing structure in engine mode selection mechanism and design method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811538288.2A CN109404546B (en) | 2018-12-16 | 2018-12-16 | Sealing structure in engine mode selection mechanism and design method |
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| Publication Number | Publication Date |
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| CN109404546A CN109404546A (en) | 2019-03-01 |
| CN109404546B true CN109404546B (en) | 2020-12-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811538288.2A Active CN109404546B (en) | 2018-12-16 | 2018-12-16 | Sealing structure in engine mode selection mechanism and design method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110513218A (en) * | 2019-09-12 | 2019-11-29 | 中北大学 | Sealing structure and design method in a kind of engine mode selection mechanism |
| CN113719623B (en) * | 2021-09-15 | 2023-09-22 | 中国航空发动机研究院 | Valve for annular channel of aero-engine |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US5035214A (en) * | 1990-02-16 | 1991-07-30 | Siemens Automotive L.P. | Engine throttle blade sealing |
| DE102009015183B4 (en) * | 2009-03-31 | 2014-04-17 | Pierburg Gmbh | flap valve |
| CN203740126U (en) * | 2014-03-31 | 2014-07-30 | 冯加伟 | Morphing aircraft with wide flight envelope |
| CN103939219B (en) * | 2014-04-24 | 2016-01-27 | 北京航空航天大学 | Mode switching valve in a kind of variable cycle engine adjusting mechanism |
| CN107524475B (en) * | 2016-06-21 | 2019-07-26 | 中国航发商用航空发动机有限责任公司 | Turbine guide vane, turbine and aero-engine |
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