CN114017561B - Sealing structure suitable for aerospace engine pipeline - Google Patents

Sealing structure suitable for aerospace engine pipeline Download PDF

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Publication number
CN114017561B
CN114017561B CN202111371733.2A CN202111371733A CN114017561B CN 114017561 B CN114017561 B CN 114017561B CN 202111371733 A CN202111371733 A CN 202111371733A CN 114017561 B CN114017561 B CN 114017561B
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pipeline
sealing
sealing lip
lip
sealing ring
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CN114017561A (en
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李智军
闫方琦
常涛
牛晋波
宋勇
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Xian Aerospace Propulsion Institute
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Xian Aerospace Propulsion Institute
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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
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L23/00—Flanged joints
    • F16L23/16—Flanged joints characterised by the sealing means
    • F16L23/18—Flanged joints characterised by the sealing means the sealing means being rings
    • F16L23/20—Flanged joints characterised by the sealing means the sealing means being rings made exclusively of metal
    • 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
    • F16J9/00—Piston-rings, e.g. non-metallic piston-rings, seats therefor; Ring sealings of similar construction
    • F16J9/12—Details
    • F16J9/20—Rings with special cross-section; Oil-scraping rings
    • 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
    • F16J9/00—Piston-rings, e.g. non-metallic piston-rings, seats therefor; Ring sealings of similar construction
    • F16J9/26—Piston-rings, e.g. non-metallic piston-rings, seats therefor; Ring sealings of similar construction characterised by the use of particular materials

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  • Engineering & Computer Science (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Gasket Seals (AREA)

Abstract

The invention discloses a sealing structure suitable for an aerospace engine pipeline, which comprises a first pipeline provided with a first flange and a second pipeline provided with a second flange, wherein the first pipeline is provided with a first flange; the first flange and the second flange are in butt joint and are fixedly connected with the first pipeline and the second pipeline; a metal sealing ring is arranged between the first flange and the second flange; the metal seal ring includes an inner seal lip and an outer seal lip; one end of the inner sealing lip is connected with one end of the outer sealing lip to form a closed end of the metal sealing ring, the other end of the inner sealing lip is kept away from one end of the outer sealing lip to form an open end of the metal sealing ring, the other end of the inner sealing lip is in interference fit with the outer circular surface of the first pipeline, and the other end of the outer sealing lip is in interference fit with the outer circular surface of the second pipeline; the open end faces the direction of the incoming flow of the medium; the sealing structure has a self-tightening function, can self-compensate the deformation of the pipeline and the flange, reduces the leakage risk and solves the problem of axial leakage.

Description

Sealing structure suitable for aerospace engine pipeline
Technical Field
The invention belongs to the field of metal sealing, and particularly relates to a metal V-shaped sealing structure suitable for an aerospace engine pipeline.
Background
The metal seal is used as a reliable seal form and is widely applied to various fields, in particular to the field of flange seal of an aerospace engine pipeline. The conventional metal sealing forms of the flange are mainly solid gaskets or O, C and V-shaped sealing rings, the above sealing structures can solve the problem of radial leakage, and the sealing effect for axial leakage is very limited.
Disclosure of Invention
The invention provides a sealing structure suitable for an aerospace engine pipeline, which aims to solve the problem that an O-shaped sealing ring, a C-shaped sealing ring and an existing V-shaped sealing structure cannot meet the axial sealing requirement of a flange joint of the aerospace engine pipeline.
The basic practical principle of the invention is as follows:
the invention combines the working condition of an aerospace engine and a sealing medium, analyzes the sealing working state, and provides a metal sealing ring structure: when the sealing structure is assembled to the pipeline, the metal sealing ring is subjected to pretightening force, and even if the metal sealing ring is elastically deformed or slightly plastically deformed, the inner sealing lip is in interference fit with the first pipeline, the outer sealing lip is in interference fit with the second pipeline, and certain contact pressure is generated to form initial sealing force;
when the sealing structure works, the medium pressure can enter the metal sealing ring, so that the inner sealing lip and the outer sealing lip are outwards opened, the contact pressure between the inner sealing lip and the first pipeline and the second pipeline is further increased, the self-tightening effect is generated, the sealing capability is enhanced, the sealing performance reduction of the pipeline caused by temperature deformation, bolt stretching deformation and other reasons can be compensated, the leakage risk is reduced, and therefore the effective axial sealing of the flange connection part of the aerospace engine pipeline is realized.
The specific technical scheme of the invention is as follows:
a sealing structure suitable for an aerospace engine pipeline, wherein the engine pipeline comprises a first pipeline provided with a first flange and a second pipeline provided with a second flange; one end of the first pipeline extends into the second pipeline for communication; the first flange and the second flange are in butt joint and are fixedly connected with the first pipeline and the second pipeline;
the improvement is that:
a metal sealing ring is arranged between the first flange and the second flange;
the metal seal ring includes an inner seal lip and an outer seal lip; one end of the inner sealing lip is connected with one end of the outer sealing lip to form a closed end of the metal sealing ring, the other end of the inner sealing lip is kept away from one end of the outer sealing lip to form an open end of the metal sealing ring, the other end of the inner sealing lip is in interference fit with the outer circular surface of the first pipeline, and the other end of the outer sealing lip is in interference fit with the outer circular surface of the second pipeline;
the open end faces the direction of the incoming flow of the medium;
the metal sealing ring material is determined by the medium temperature, and when the medium is high temperature, the metal sealing ring material is a high temperature alloy; and when the low-temperature medium is used, the material of the metal sealing ring is stainless steel or high-temperature alloy.
Further, the surfaces of the inner seal lip and the outer seal lip are plated or sprayed, and the thickness of the plating layer is 10-120 mu m.
Further, the included angle alpha between the inner sealing lip and the outer sealing lip is 30-45 degrees.
Further, the thickness d of the inner sealing lip and the outer sealing lip is 0.15 mm-0.5 mm.
Further, the interference magnitude of the other end of the inner sealing lip and the outer circular surface of the first pipeline and the interference magnitude W of the other end of the outer sealing lip and the outer circular surface of the second pipeline are both 0.05 mm-0.2 mm.
Further, the contact end of the outer sealing lip and the outer circular surface of the second pipeline is provided with a round angle r, and the radius range of the round angle r is 0.04-0.1 mm;
the arc-shaped radius r of the inner sealing lip and the outer sealing lip is 0.04 mm-0.1 mm.
Further, when the medium temperature is more than or equal to 730 ℃ and less than or equal to 870 ℃, the material model of the metal sealing ring is GH4141; the medium temperature is less than or equal to 630 ℃ and less than or equal to 730 ℃, and the material model is GH4738; the medium temperature is more than or equal to 450 ℃ and less than or equal to 630 ℃, and the material model is GH4169; the temperature of the medium is less than or equal to 450 ℃, and the material model is GH4145;
in a low-temperature environment, the medium temperature is more than or equal to minus 196 ℃, and the material model of the metal sealing ring is 07Cr16Ni6 or GH4169.
Further, the surface roughness Ra of the inner seal lip and the outer seal lip is less than or equal to 0.8 mu m.
Further, the specific design method of the metal sealing ring is as follows:
step 1: determining the material of the metal sealing ring according to the medium temperature;
step 2: determining an initial radius R of the sealing ring and a sealing height h according to the position and the requirement for installing the sealing, and setting an initial interference W according to the working condition of the sealing;
step 3: the included angle alpha between the inner sealing lip and the outer sealing lip is calculated according to the following formula;
Figure BDA0003362490560000031
I＝π[R 4 -(R-d1-d2) 4 ] (2)
Figure BDA0003362490560000032
wherein h is the height of the sealing ring;
e is the elastic modulus of the sealing ring material;
i is the cross-section moment of inertia of the sealing ring material
d1 is the material thickness;
d2 is the thickness of the coating;
f is the pressure of the medium applied to the sealing arm;
p is the medium pressure;
step 4: adjusting the calculated included angle alpha to be an integer value according to the rounding principle;
step 5: according to the integral included angle value and the formulas (1), (2) and (3) in the step 3, the actual interference value W is reversely deduced Real world ；
Step 6: according to the interference value W Real world The sealing lip fillet r is determined, and the specific solving formula is as follows:
Figure BDA0003362490560000033
compared with the prior art, the invention has the following beneficial effects:
1. the elastic self-tightening mechanism has the advantages of high pressure bearing capacity and high compensation capacity. According to the metal sealing structure, the inner sealing lip and the outer sealing lip are tightly attached to the first pipeline and the second pipeline respectively by utilizing the pressure of a leakage medium, so that the metal sealing structure has a self-tightening function, the sealing capability is enhanced, the deformation of the pipeline and the flange caused by temperature and bolt stretching can be self-compensated, the leakage risk is greatly reduced, the problem of axial leakage possibly occurring at the flange connection part of the aerospace engine pipeline is effectively solved, and the metal sealing structure has important application value in the aerospace field.
2. The universality is good and the applicability is wide. The metal sealing structure consists of an inner sealing lip and an outer sealing lip, has a simple structure, is determined by medium temperature, can adapt to sealing scenes of axial leakage under various working conditions, has a wide applicable temperature range (-253-870 ℃), and is applicable to various types of mediums including liquid hydrogen, liquid oxygen, methane, oxygen-enriched fuel gas, dinitrogen tetroxide, hydrazine mediums, water, nitrogen, air, kerosene, fuel oil and the like.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
fig. 2 is a schematic structural view of a metal seal ring.
FIG. 3 is a schematic view of a partial structure of a specific installation area of a metal seal ring;
reference numerals:
1-first pipeline, 11 first flange, 2-second pipeline, 21-second flange, 3-annular chamber, 4-metal sealing ring, 41-inner sealing lip, 42-outer sealing lip.
Detailed Description
So that the manner in which the above recited objects, features and advantages of the present invention can be understood in detail, a more particular description of the invention, briefly summarized above, may be had by reference to the embodiments, some of which are illustrated in the appended drawings. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments of the present invention without making any inventive effort, shall fall within the scope of the present invention.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention, but the present invention may be practiced in other ways other than those described herein, and persons skilled in the art will readily appreciate that the present invention is not limited to the specific embodiments disclosed below.
Also in the description of the present invention, it should be noted that the orientation or positional relationship indicated by the terms "upper, lower, inner and outer", etc. are based on the orientation or positional relationship shown in the drawings, are merely for convenience of describing the present invention and simplifying the description, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first, second, or third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
The terms "mounted, connected, and coupled" should be construed broadly in this disclosure unless otherwise specifically indicated and defined, such as: can be fixedly connected, detachably connected or integrally connected: it may also be a mechanical connection, an electrical connection, or a direct connection, or may be indirectly connected through an intermediate medium, or may be a communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
As shown in fig. 1, the specific structure of the sealing structure when the sealing structure is used on an aerospace engine pipeline is as follows:
the engine pipeline comprises a first pipeline 1 provided with a first flange 11 and a second pipeline 2 provided with a second flange 21; one end of the first pipeline 1 extends into the second pipeline 2 for communication; the first flange 11 and the second flange 21 are in butt joint for fixedly connecting the first pipeline 1 and the second pipeline 2; an annular chamber 3 is formed among the first pipeline 1, the second pipeline 2, the first flange 21 and the second flange 22, and a metal sealing ring 4 is arranged in the annular chamber 3;
as shown in fig. 2 and 3, the metal seal ring 4 includes an inner seal lip 41 and an outer seal lip 42; one end of the inner sealing lip 41 is connected with one end of the outer sealing lip 42 to form a closed end of the metal sealing ring, a distance is kept between the other end of the inner sealing lip 41 and the other end of the outer sealing lip 42 to form an open end of the metal sealing ring, the open end faces the incoming flow direction of the medium (as shown in fig. 1, namely, the open end faces the arrow direction, so that the leaked medium can enter the metal sealing ring), the other end of the inner sealing lip 41 is in interference fit with the outer circular surface of the first pipeline 1, and the other end of the outer sealing lip 42 is in interference fit with the outer circular surface of the second pipeline 2;
the metal sealing ring material is determined by the medium temperature, and when the medium is high temperature, the metal sealing ring material is a high temperature alloy; when in low-temperature medium, the metal sealing ring material is stainless steel or high-temperature alloy, and the specific selection principle of the material is as follows:
the temperature of the medium is less than or equal to 870 ℃, and the material model of the metal sealing ring is GH4141; the temperature of the medium is less than or equal to 730 ℃, and the material model of the metal sealing ring is GH4738; the temperature of the medium is less than or equal to 630 ℃, and the material model of the metal sealing ring is GH4169; the temperature of the medium is less than or equal to 450 ℃, and the material model of the metal sealing ring is GH4145; in a low-temperature environment, the metal sealing ring is made of 07Cr16Ni6 and GH4169.
When the metal sealing ring is installed in the annular cavity, the metal sealing ring is elastically deformed or slightly plastically deformed to generate certain contact pressure to form an initial sealing force;
when the metal sealing ring works, the sealing ring is opened by the aid of medium pressure, self-tightening effect is generated, contact pressure is further increased, sealing capacity is improved, and the sealing ring structure can self-compensate deformation of a pipeline and a flange caused by temperature and bolt stretching, so that leakage risks are reduced.
Besides the installation position, the structural shape and the material of the metal sealing ring in the pipeline, the included angle between the inner sealing lip and the outer sealing lip, the thickness of the metal sealing ring, the interference between the inner sealing lip and the outer sealing lip and between the outer sealing lip and the outer sealing lip of the outer sealing lip are also important factors affecting the final sealing effect.
The specific design process of the metal sealing ring is as follows:
step 1: determining the material of the metal sealing ring according to the medium temperature;
step 2: determining an initial radius R of the sealing ring and a sealing height h according to the position and the requirement of the sealing to be installed, and presuming an initial interference W according to the working condition (pressure, temperature and medium attribute) of the sealing;
step 3: the included angle alpha between the inner sealing lip and the outer sealing lip is calculated according to the following formula;
Figure BDA0003362490560000061
I＝π[R 4 -(R-d1-d2) 4 ](2)
Figure BDA0003362490560000062
wherein h is the height of the sealing ring;
e is the elastic modulus of the sealing ring material;
i is the cross-section moment of inertia of the sealing ring material
d1 is the material thickness;
d2 is the thickness of the coating;
f is the pressure of the medium applied to the sealing arm;
p is the medium pressure;
step 4: because the calculated included angle alpha is not necessarily an integer, the calculated included angle alpha needs to be subjected to integer processing (according to the rounding principle) in order to ensure the producibility of the metal sealing ring;
according to the integral included angle value and the formulas (1), (2) and (3) in the step 3, the actual interference value W is reversely deduced Real world ；
Step 6: according to the interference value W Real world The sealing lip fillet r is determined, and the specific solving formula is as follows:
Figure BDA0003362490560000071
in order to further obtain the optimal value range of parameters such as the included angle between the inner sealing lip and the outer sealing lip, the interference between the inner sealing lip and the outer sealing lip and between the inner sealing lip and the first pipeline and between the outer sealing lip and the second pipeline respectively, and the radius of a round corner at the contact end of the outer sealing lip and the outer circle surface of the second pipeline, the invention also performs the following experimental analysis:
in order to verify the included angle between the inner sealing lip and the outer sealing lip, the thickness of the metal sealing ring, the interference between the inner sealing lip and the outer sealing lip and between the outer sealing lip and the outer sealing lip of the second pipeline respectively, and the radius of the round corner of the contact end of the outer sealing lip and the outer sealing lip of the second pipeline are measured, the simulation test is carried out, and the simulation result is shown in the following table:
Figure BDA0003362490560000072
Figure BDA0003362490560000081
according to the table, the leakage is taken as an evaluation index to carry out extremely poor analysis, the interference influence degree is maximum, the included angle alpha is second, the influence of the round angle r is smaller, the influence degree of d is minimum, the extremely poor is subjected to multi-factor evaluation, the optimal range is that the opening included angle alpha is 30-45 degrees, the material thickness d is 0.15-0.5 mm, the radius range of the round angle r is 0.04-0.1 mm, and the interference value is 0.05-0.25 mm.
The foregoing disclosure is merely illustrative of specific embodiments of the invention, but the embodiments are not limited thereto and variations within the scope of the invention will be apparent to those skilled in the art.

Claims (8)

1. A sealing structure suitable for an aerospace engine pipeline, wherein the engine pipeline comprises a first pipeline provided with a first flange and a second pipeline provided with a second flange; one end of the first pipeline extends into the second pipeline for communication; the first flange and the second flange are in butt joint and are fixedly connected with the first pipeline and the second pipeline;
the method is characterized in that:
a metal sealing ring is arranged between the first flange and the second flange;
the metal seal ring includes an inner seal lip and an outer seal lip; one end of the inner sealing lip is connected with one end of the outer sealing lip to form a closed end of the metal sealing ring, the other end of the inner sealing lip is kept away from one end of the outer sealing lip to form an open end of the metal sealing ring, the other end of the inner sealing lip is in interference fit with the outer circular surface of the first pipeline, and the other end of the outer sealing lip is in interference fit with the outer circular surface of the second pipeline;
the open end faces the direction of the incoming flow of the medium;
the metal sealing ring material is determined by the medium temperature, and when the medium is high temperature, the metal sealing ring material is a high temperature alloy; when in a low-temperature medium, the material of the metal sealing ring is stainless steel or high-temperature alloy;
the specific design method of the metal sealing ring is as follows:
step 1: determining the material of the metal sealing ring according to the medium temperature;
step 2: determining an initial radius R of the sealing ring and a sealing height h according to the position and the requirement for installing the sealing, and setting an initial interference W according to the working condition of the sealing;
step 3: the included angle alpha between the inner sealing lip and the outer sealing lip is calculated according to the following formula;
Figure QLYQS_1
I＝π[R 4 -(R-d1-d2) 4 ] (2)
Figure QLYQS_2
wherein h is the height of the sealing ring;
e is the elastic modulus of the sealing ring material;
i is the cross-sectional moment of inertia of the sealing ring material;
d1 is the material thickness;
d2 is the thickness of the coating;
f is the pressure of the medium applied to the sealing arm;
p is the medium pressure;
step 4: adjusting the calculated included angle alpha to be an integer value according to the rounding principle;
step 5: according to the integral included angle valueAnd formulas (1), (2) and (3) of the step 3, reversely deducing an actual interference value W Real world ；
Step 6: according to the interference value W Real world The sealing lip fillet r is determined, and the specific solving formula is as follows:
Figure QLYQS_3
2. the sealing structure suitable for use in an aerospace engine pipeline according to claim 1, wherein: the surfaces of the inner sealing lip and the outer sealing lip are plated or sprayed, and the thickness of the plating layer is 10-120 mu m.
3. The sealing structure suitable for use in an aerospace engine pipeline according to claim 1, wherein: the included angle alpha between the inner sealing lip and the outer sealing lip is 30-45 degrees.
4. The sealing structure suitable for use in an aerospace engine pipeline according to claim 1, wherein: the thickness d of the inner sealing lip and the outer sealing lip is 0.15 mm-0.5 mm.
5. The sealing structure suitable for use in an aerospace engine pipeline according to claim 1, wherein: the interference magnitude of the other end of the inner sealing lip and the outer circular surface of the first pipeline and the interference magnitude W of the other end of the outer sealing lip and the outer circular surface of the second pipeline are both 0.05 mm-0.2 mm.
6. The sealing structure suitable for use in an aerospace engine pipeline according to claim 1, wherein: the contact end of the outer sealing lip and the outer circular surface of the second pipeline is provided with a round angle r, and the radius range of the round angle r is 0.04-0.1 mm;
the arc-shaped radius r of the inner sealing lip and the outer sealing lip is 0.04 mm-0.1 mm.
7. The sealing structure suitable for use in an aerospace engine pipeline according to claim 1, wherein: when the medium temperature is more than or equal to 730 ℃ and less than or equal to 870 ℃, the material model of the metal sealing ring is GH4141; the medium temperature is less than or equal to 630 ℃ and less than or equal to 730 ℃, and the material model is GH4738; the medium temperature is more than or equal to 450 ℃ and less than or equal to 630 ℃, and the material model is GH4169; the temperature of the medium is less than or equal to 450 ℃, and the material model is GH4145;
in a low-temperature environment, the medium temperature is more than or equal to minus 196 ℃, and the material model of the metal sealing ring is 07Cr16Ni6 or GH4169.
8. The sealing structure suitable for use in an aerospace engine pipeline according to claim 1, wherein: the surface roughness Ra of the inner sealing lip and the outer sealing lip is less than or equal to 0.8 mu m.
CN202111371733.2A 2021-11-18 2021-11-18 Sealing structure suitable for aerospace engine pipeline Active CN114017561B (en)

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Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3839843C2 (en) * 1988-11-25 1995-04-06 Mtu Muenchen Gmbh Shaft seal for turbomachinery, especially gas turbine engines
JP2000055207A (en) * 1998-08-10 2000-02-22 Nok Corp Sealing device
CN105697786B (en) * 2016-04-18 2017-09-22 北京裕泰行新材料科技有限公司 Ultralow temperature sealing ring
CN207762394U (en) * 2017-12-19 2018-08-24 潍柴动力股份有限公司 Medium pipeline sealing structure
CN211315404U (en) * 2019-09-30 2020-08-21 潍柴动力股份有限公司 Sealing element for engine exhaust pipe and exhaust pipe group
CN213685715U (en) * 2020-08-31 2021-07-13 天津市凯诺实业有限公司 Elastic metal sealing ring

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