CN114992331A - Dynamic sealing structure for thin wall of swinging nozzle of solid rocket engine - Google Patents
Dynamic sealing structure for thin wall of swinging nozzle of solid rocket engine Download PDFInfo
- Publication number
- CN114992331A CN114992331A CN202210774370.5A CN202210774370A CN114992331A CN 114992331 A CN114992331 A CN 114992331A CN 202210774370 A CN202210774370 A CN 202210774370A CN 114992331 A CN114992331 A CN 114992331A
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- Prior art keywords
- sealing
- rocket engine
- solid rocket
- nozzle
- thin wall
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Classifications
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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
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/46—Sealings with packing ring expanded or pressed into place by fluid pressure, e.g. inflatable packings
- F16J15/48—Sealings with packing ring expanded or pressed into place by fluid pressure, e.g. inflatable packings influenced by the pressure within the member to be sealed
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/97—Rocket nozzles
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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
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
- F16J15/10—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with non-metallic packing
- F16J15/102—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces with non-metallic packing characterised by material
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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
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/16—Sealings between relatively-moving surfaces
- F16J15/162—Special parts or details relating to lubrication or cooling of the sealing itself
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Architecture (AREA)
- Fluid Mechanics (AREA)
- Gasket Seals (AREA)
Abstract
The invention discloses a dynamic sealing structure for a thin wall of a swinging nozzle of a solid rocket engine, which comprises a movable ball body, a sealing ball seat, a V-shaped metal sealing ring and a sealing ball cover, wherein the movable ball body is arranged on the sealing ball seat, the sealing ball seat is connected with the sealing ball cover through a screw 5, and the V-shaped metal sealing ring is arranged in a rectangular area formed by the sealing ball seat, the sealing ball cover and the movable ball body. The invention has the characteristics of high reliability, good sealing effect, simple result and the like; the V-shaped metal sealing ring can adapt to higher temperature, the surface of the sealing ring is sprayed with a non-metal material, the sealing ring has better self-lubricating property, can bring smaller friction coefficient, and ensures good sealing effect in the process of multiple swinging.
Description
Technical Field
The invention belongs to the technical field of adjustable nozzles of aerospace solid rocket engines, and particularly relates to a dynamic sealing structure for a thin wall of a swinging nozzle of a solid rocket engine.
Background
The solid rocket engine is used as a power device of an aircraft, and thrust control is required to be carried out according to different requirements of the aircraft, wherein the thrust control comprises control of the thrust direction, the thrust magnitude and the thrust termination. The solid rocket engine is mainly implemented through a spray pipe of the solid rocket engine, and the technical difficulty is great. At present, flexible nozzles and bearing oscillating nozzles are the main research directions of adjustable nozzles. In the field of bearing swinging spray pipes, but the development of adjustable spray pipes is limited by the dynamic sealing technology.
At present, structures such as carbon-phenolic resin sealing rings or polytetrafluoroethylene jackets are mainly adopted, and certain hidden dangers exist in the adjustable spray pipe with high temperature, multi-swing and quick response due to the characteristics of nonmetal, so that the development of the bearing swing spray pipe technology is restricted.
Disclosure of Invention
In view of the above, the main object of the present invention is to provide a thin-walled dynamic seal structure for a swinging nozzle of a solid rocket engine.
In order to achieve the purpose, the technical scheme of the invention is realized as follows:
the embodiment of the invention provides a dynamic sealing structure for a thin wall of a swinging nozzle of a solid rocket engine, which comprises a movable ball body, a sealing ball seat, a V-shaped metal sealing ring and a sealing ball cover, wherein the movable ball body is arranged on the sealing ball seat, the sealing ball seat is connected with the sealing ball cover through a screw 5, and the V-shaped metal sealing ring is arranged in a rectangular area formed by the sealing ball seat, the sealing ball cover and the movable ball body.
In the scheme, a flexible graphite ring is arranged at the joint of the sealing ball seat and the sealing ball cover.
In the above scheme, the sealing ball seat, the sealing ball cover and the movable ball body are concentric.
In the above solution, the V-shaped metal sealing ring includes a base and a V-shaped corner, the base is provided with the V-shaped corner, and one side of the V-shaped corner is provided with an inner side joint area and the other side is provided with an outer side joint area.
In the above scheme, the bending radius and the wall thickness of the inner attaching area are determined according to the space and the pressure.
In the above scheme, the bending radius and the wall thickness of the inner side attaching area are determined according to the space and the pressure, and specifically: the material stress concentration coefficient is determined according to the formula S ═ P ^ 2 ^ R/(4 ^ sigma ^ theta) + C, wherein S is the wall thickness, P is the working pressure, R is the bending radius, [ sigma ] is the material allowable stress, theta is the material stress concentration coefficient, and C is the wall thickness accessory quantity.
In the scheme, the V-shaped angle is calculated, and an appropriate angle is selected, so that the V-shaped metal sealing ring generates enough compression.
In the above scheme, the V-shaped angle is calculated to select a proper angle, specifically: determined according to the formula α ═ 2 § arc tan (2 § a § h), wherein a represents the sealing ring area, α represents the angle of the V-shaped angle, α represents the sealing ring compression ratio, and h represents the depth of the V-shaped angle.
In the above scheme, the base is laminated with the bottom surface of sealed ball seat, inboard laminating district, outside laminating district all with sealed ball seat and spray tube laminate closely.
Compared with the prior art, the invention has the characteristics of high reliability, good sealing effect, simple result and the like; the V-shaped metal sealing ring can adapt to higher temperature, the surface of the sealing ring is sprayed with a non-metal material, the sealing ring has better self-lubricating property, can bring smaller friction coefficient, and ensures good sealing effect in the process of multiple swinging.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and do not limit the invention. In the drawings:
FIG. 1 is a schematic structural diagram of an embodiment of the present invention;
FIG. 2 is a view illustrating a V-shaped metal seal ring according to an embodiment of the present invention;
FIG. 3 is a structural diagram of a flexible graphite ring according to an embodiment of the present invention;
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The same or similar reference numerals in the drawings of the present embodiment correspond to the same or similar components; in the description of the present invention, it is to be understood that the terms "upper", "lower", "left", "right", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred devices or elements must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, the terms describing the positional relationships in the drawings are only for illustrative purposes and are not to be construed as limitations of the present patent, and specific meanings of the terms may be understood by those skilled in the art according to specific situations.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a process, article, or apparatus that comprises the element.
The embodiment of the invention provides a wear-resistant high-temperature-resistant thin-wall dynamic sealing structure for a swinging nozzle of a solid rocket engine, which comprises a movable ball body 1, a sealing ball seat 2, a V-shaped metal sealing ring 3 and a sealing ball cover 6, wherein the movable ball body 1 is arranged on the sealing ball seat 2, the sealing ball seat 2 is connected with the sealing ball cover 6 through a screw 5, and the V-shaped metal sealing ring 3 is arranged in a rectangular area formed by the sealing ball seat 2, the sealing ball cover 6 and the movable ball body 1.
And a flexible graphite ring 4 is arranged at the joint of the sealing ball seat 2 and the sealing ball cover 6.
The outer side of the V-shaped metal seal 3 is provided with a non-metal coating, so that the sealing performance in the rotating process can be ensured.
Installing a V-shaped metal sealing ring 3, wherein the opening of the V-shaped metal sealing ring faces to the air inlet side; in the working process, the V-shaped metal sealing ring 3 is opened with a certain opening by pressure, so that the sealing performance is ensured.
V-arrangement metal seal ring 3 includes base 31, V type angle 32, set up V type angle 32 on the base 31, one side is provided with inboard laminating district 33, the opposite side is provided with outside laminating district 34 on the V type angle 32.
The bending radius and the wall thickness of the inner attachment zone 33 are determined according to the space and the pressure.
Specifically, the bending radius and the wall thickness of the inner attaching area 33 are determined according to the space and the pressure, specifically: the material stress concentration coefficient is determined according to the formula S ═ P ^ 2 ^ R/(4 ^ sigma ^ theta) + C, wherein S is the wall thickness, P is the working pressure, R is the bending radius, [ sigma ] is the material allowable stress, theta is the material stress concentration coefficient, and C is the wall thickness accessory quantity.
The V-angle 32 is calculated and selected to be an appropriate angle to allow sufficient compression of the V-shaped metal seal ring 3. Specifically, the V-shaped angle 32 is calculated to select a suitable angle, specifically: determined according to the formula α ═ 2 · arc tan (2 · § a § h), where a is the seal ring area, α is the angle of V-shaped angle 32, § is the seal ring compression ratio, and h is the depth of V-shaped angle 32.
When in use, the base 31 is attached to the bottom surface of the sealing ball seat 2, and the inner attaching area 33 and the outer attaching area 34 are closely attached to the sealing ball seat 2 and the spray pipe; during operation, the outer bonding area 34 is tightly bonded to provide good sealing through pressure, the inner bonding area 33 is bonded to the curved surface of the spray pipe, and along with rotation of the spray pipe, a good bonding effect is ensured through pressure, so that a good sealing effect is provided.
The V-shaped sealing ring 3 needs to ensure the attaching force and the attaching area of two sides in the working process because one side is a metal surface and the other side is a non-metal curved surface. As can be seen from figure 2, the end part of the V-shaped sealing ring 3 is thin in the working process, the V-shaped sealing ring belongs to point contact when the pressure is low, the sealing effect is achieved, the end part is slightly deformed when the pressure is high, the attaching area is improved, the sealing effect is ensured, and the sealing effect is better if the pressure is high.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention.
Claims (9)
1. The dynamic sealing structure for the thin wall of the swinging nozzle of the solid rocket engine is characterized by comprising a movable ball body, a sealing ball seat, a V-shaped metal sealing ring and a sealing ball cover, wherein the movable ball body is arranged on the sealing ball seat, the sealing ball seat is connected with the sealing ball cover through a screw 5, and the V-shaped metal sealing ring is arranged in a rectangular area formed by the sealing ball seat, the sealing ball cover and the movable ball body.
2. The dynamic seal structure for the thin wall of the swinging nozzle of the solid rocket engine according to claim 1, wherein a flexible graphite ring is arranged at the joint of the sealing ball seat and the sealing ball cover.
3. The dynamic seal structure for the thin wall of the swinging nozzle of the solid rocket engine according to claim 1 or 2, wherein the seal ball seat, the seal ball cover and the movable ball body are concentric.
4. The dynamic sealing structure for the thin wall of the pendular nozzle of a solid rocket engine as recited in claim 3, wherein said V-shaped metal sealing ring comprises a base and a V-shaped corner, said base is provided with a V-shaped corner, one side of said V-shaped corner is provided with an inner side bonding region, and the other side of said V-shaped corner is provided with an outer side bonding region.
5. The dynamic seal structure for the thin wall of the pendular nozzle of a solid rocket engine as recited in claim 4, wherein the bending radius and the wall thickness of said inboard landing zone are determined by space and pressure.
6. The dynamic seal structure for the thin wall of the oscillating nozzle of the solid rocket engine according to claim 5, wherein the bending radius and the wall thickness of the inner bonding area are determined according to space and pressure, and specifically: the material stress concentration coefficient is determined according to the formula S ═ P ^ 2 ^ R/(4 ^ sigma ^ theta) + C, wherein S is the wall thickness, P is the working pressure, R is the bending radius, [ sigma ] is the material allowable stress, theta is the material stress concentration coefficient, and C is the wall thickness accessory quantity.
7. The dynamic seal structure for a thin wall of a solid rocket engine pendular nozzle of claim 5 wherein said V-shaped angle is calculated and selected to be an appropriate angle to allow a sufficient amount of compression of the V-shaped metal seal ring.
8. The dynamic seal structure for the thin wall of the pendular nozzle of a solid rocket engine as recited in claim 7, wherein said V-shaped angle is calculated by selecting a suitable angle, specifically: the sealing ring compression ratio is determined according to a formula of a ═ 2 § arctan (2 § a § h), wherein a is the sealing ring area, a is the angle of the V-shaped angle, a is the sealing ring compression ratio, and h is the depth of the V-shaped angle.
9. The dynamic seal structure for the thin wall of the pendular nozzle of a solid rocket engine as recited in claim 8, wherein said base is attached to the bottom surface of said sealing ball seat, and said inner and outer attachment areas are both closely attached to said sealing ball seat and said nozzle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210774370.5A CN114992331A (en) | 2022-07-01 | 2022-07-01 | Dynamic sealing structure for thin wall of swinging nozzle of solid rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210774370.5A CN114992331A (en) | 2022-07-01 | 2022-07-01 | Dynamic sealing structure for thin wall of swinging nozzle of solid rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114992331A true CN114992331A (en) | 2022-09-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210774370.5A Pending CN114992331A (en) | 2022-07-01 | 2022-07-01 | Dynamic sealing structure for thin wall of swinging nozzle of solid rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114992331A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117145654A (en) * | 2023-10-27 | 2023-12-01 | 西安现代控制技术研究所 | Low-cost bullet tail heat-proof sealing structure capable of adapting to deformation of spray pipe |
-
2022
- 2022-07-01 CN CN202210774370.5A patent/CN114992331A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117145654A (en) * | 2023-10-27 | 2023-12-01 | 西安现代控制技术研究所 | Low-cost bullet tail heat-proof sealing structure capable of adapting to deformation of spray pipe |
| CN117145654B (en) * | 2023-10-27 | 2024-03-15 | 西安现代控制技术研究所 | Low-cost bullet tail heat-proof sealing structure capable of adapting to deformation of spray pipe |
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