CN115264536A - Ceramic matrix composite flame tube connecting device, aircraft engine and aircraft - Google Patents
Ceramic matrix composite flame tube connecting device, aircraft engine and aircraft Download PDFInfo
- Publication number
- CN115264536A CN115264536A CN202110479983.1A CN202110479983A CN115264536A CN 115264536 A CN115264536 A CN 115264536A CN 202110479983 A CN202110479983 A CN 202110479983A CN 115264536 A CN115264536 A CN 115264536A
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- ring
- ceramic matrix
- matrix composite
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- cap
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- 239000011153 ceramic matrix composite Substances 0.000 title claims abstract description 32
- 239000000463 material Substances 0.000 claims abstract description 14
- 230000000694 effects Effects 0.000 claims description 15
- 235000017166 Bambusa arundinacea Nutrition 0.000 claims description 11
- 235000017491 Bambusa tulda Nutrition 0.000 claims description 11
- 241001330002 Bambuseae Species 0.000 claims description 11
- 235000015334 Phyllostachys viridis Nutrition 0.000 claims description 11
- 239000011425 bamboo Substances 0.000 claims description 11
- 238000006073 displacement reaction Methods 0.000 abstract description 8
- 230000002035 prolonged effect Effects 0.000 abstract description 6
- 238000007789 sealing Methods 0.000 description 18
- 239000002131 composite material Substances 0.000 description 10
- 239000002184 metal Substances 0.000 description 8
- 239000000956 alloy Substances 0.000 description 7
- 238000012423 maintenance Methods 0.000 description 4
- 229910045601 alloy Inorganic materials 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 3
- 241001391944 Commicarpus scandens Species 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 239000000112 cooling gas Substances 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 230000000670 limiting effect Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 238000005452 bending Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/60—Support structures; Attaching or mounting means
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Cylinder Crankcases Of Internal Combustion Engines (AREA)
Abstract
The invention discloses a ceramic matrix composite material flame tube connecting device, an aircraft engine and an aircraft, wherein the ceramic matrix composite material flame tube connecting device comprises at least one tube ring, at least one cap and a plurality of buckle parts, one ends of the buckle parts are respectively connected to two sides of the cap through fasteners, the other ends of the buckle parts extend outwards and bend along opposite directions, so that a movable cavity is formed between the end surface of the cap and the buckle parts, the end part of the tube ring is provided with a convex part extending outwards along the radial direction of the tube ring, the movable cavity is sleeved on the convex part, so that the convex part moves in the movable cavity and limits the convex part to be separated from the movable cavity, and the tube ring is made of a ceramic matrix composite material. The cap can realize axial and radial assembly positioning of the cylinder ring through the buckle component, the cylinder ring can have displacement spaces in all directions through the movable cavity, the stress borne by the cylinder ring is effectively reduced in a thermal state, the failure risk is reduced, and the service life is greatly prolonged.
Description
Technical Field
The invention relates to a ceramic matrix composite flame tube connecting device, an aircraft engine and an aircraft.
Background
With the increasingly higher performance design index requirements of advanced aircraft engines and the increasing of the temperatures of inlets and outlets of combustion chambers, the problem that the traditional high-temperature alloy material is insufficient in temperature resistance is often exposed, and a complex air film cooling system is required to reduce the service temperature of the high-temperature alloy material. The introduction of a large amount of cooling gas can cause insufficient combustion, cause the emission of harmful gas, pollute the environment and reduce the heat efficiency of the engine.
At present, the flame tube of the main flow engine is made of high-temperature alloy materials, the allowable temperature for a long time is below 1000 ℃, and therefore a large amount of cooling air is needed to cool the wall surface of the flame tube. With the increasing requirement on the thrust of the engine, the temperature to be borne by the flame tube is gradually increased, and the high-temperature alloy cannot meet the corresponding environmental use requirement. The SiCf/SiC composite material as a ceramic matrix composite material has the characteristics of high temperature resistance, low density (about 1/3 of high-temperature alloy), oxidation resistance and the like, and the allowable temperature for a long time can reach 1200 ℃. The SiCf/SiC composite material is used as a structural material of a flame tube of a combustion chamber of a gas turbine engine, can greatly reduce the consumption of cooling gas, improves the efficiency of the engine, has great potential of reducing the weight of the engine, and has been already applied to GE9X engines in engineering.
However, the thermal expansion coefficients of the SiCf/SiC composite material and the metal material are far from each other, and the fastening member penetrates through the SiCf/SiC composite material and the metal member and is connected in a positioning manner, although a cushion block is arranged between the fastening member and the SiCf/SiC composite material at present to achieve a certain floating amount in the axial direction, the floating amount is still small, in a working state, the SiCf/SiC composite material and the metal member generate high stress at the joint of the SiCf/SiC composite material and the metal member due to different expansion amounts, and the SiCf/SiC material is lower in tensile strength and plasticity compared with a high-temperature alloy, so that the SiCf/SiC composite material is still easy to break and break, and engine failure is caused.
Disclosure of Invention
The invention aims to overcome the defects that the joint of the existing SiCf/SiC composite material and a metal piece can generate high stress, and the SiCf/SiC material has low tensile strength and plasticity, so that the SiCf/SiC composite material is easy to break and damage, and engine faults are caused, and the like, and provides a ceramic matrix composite material flame tube connecting device, an aero-engine and an aircraft.
The invention solves the technical problems through the following technical scheme:
the utility model provides a ceramic matrix composite flame tube connecting device, its characterized in that, it includes at least one section of thick bamboo ring, at least one cap and a plurality of buckle part, a plurality of buckle part's one end respectively through the fastener connect in the both sides of cap, a plurality of buckle part's the other end outwards extends and buckles along relative direction, so that the terminal surface and a plurality of cap be formed with movable chamber between the buckle part, the tip of section of thick bamboo ring has the bellying of outwards extending along its radial direction, movable chamber cover is located the bellying makes the bellying is in activity intracavity activity and restriction the bellying breaks away from movable chamber, the material of section of thick bamboo ring is ceramic matrix composite.
In this scheme, adopt above-mentioned structural style, the barrel ring passes through the bellying restriction and moves about in the activity intracavity for the cap cover passes through buckle part and realizes axial and radial positioning to the barrel ring, and realizes through the activity chamber that the barrel ring has the displacement space in each direction, has effectively reduced the stress that the barrel ring receives under the hot attitude, reduces the inefficacy risk, has improved life greatly.
Preferably, the protruding parts comprise a first protruding part and a second protruding part, and the first protruding part and the second protruding part are respectively positioned at two sides of the cylinder ring and extend outwards in opposite directions;
the first boss and the second boss are movable in the axial direction, the radial direction, and the circumferential direction of the cylinder ring in the movable chamber.
In the scheme, the structure is adopted, so that the cylinder ring is axially and radially assembled and positioned, the stress borne by the cylinder ring is effectively reduced in a hot state, the failure risk is reduced, and the service life of the ceramic matrix composite flame tube connecting device is greatly prolonged; meanwhile, the structure is simple, and the processing and the manufacturing are convenient.
Preferably, the ceramic matrix composite flame tube connecting device further comprises an elastic sealing ring, the elastic sealing ring is located in the movable cavity, and the elastic sealing ring is arranged between the buckle component and the tube ring in a pressing mode and exerts radial acting force on the buckle component and the tube ring.
In this scheme, adopt above-mentioned structural style, elasticity seals circle has certain radial packing force when the assembly for buckle part and bellying contact, and the contact surface of buckle part and bellying, the contact surface between bellying and the elasticity seals the circle all is in the state of compressing tightly, reaches sealed effect through the use of elasticity seals the circle, can realize the radial unsteady of section of thick bamboo ring simultaneously.
Preferably, the end of the cap has a protruding section, the end of the cylinder ring has a groove, and the protruding section is embedded in the groove to realize a limiting effect along the circumferential direction of the cylinder ring.
In the scheme, by adopting the structure form, the protruding section is embedded in the groove, and the metal arc-shaped protrusion can be used for circumferentially positioning the cylinder ring; meanwhile, the effect of curved surface sealing can be realized by metal expansion in a thermal state, the contact area is increased through the protruding section and the groove, and the sealing performance is improved.
Preferably, the surface shapes of the protruding section and the groove are both arc-shaped, and the protruding section is in matched contact with the groove.
In this scheme, adopt above-mentioned structural style, the contact surface is big, further improves sealed effect.
Preferably, a plurality of the snap members are provided to the cap continuously and uninterruptedly in a circumferential direction of the cap, and the snap members are detachably attached to the cap by bolts.
In the scheme, the structure is adopted, so that the buckling parts designed into a plurality of fan-shaped sections are encircled into a circle, and the assembly is convenient; meanwhile, after the local damage, only the invalid buckle part can be replaced, the maintenance is convenient, and the maintenance cost is reduced.
Preferably, in two adjacent buckle parts, one buckle part has an outward extending section, the other buckle part has an inward recessed avoidance section, and the extending section extends into the avoidance section and is abutted with the inner wall surface of the avoidance section.
In this scheme, adopt above-mentioned structural style, stretch into through stretching out the section and dodge in the section, can increase the area of contact of two adjacent buckle parts when the assembly, improve the cooperation degree.
Preferably, a gap is formed between the top end of the protruding section and the groove bottom of the avoiding section.
In this scheme, adopt above-mentioned structural style, buckle part has deformation displacement space through the clearance when displacement in the week for effectively reduced the buckle part stress that receives under the hot attitude, reduced the inefficacy risk, improved buckle part's life greatly.
An aircraft engine characterised in that it comprises a ceramic matrix composite liner attachment as described above.
In this scheme, adopt above-mentioned structural style, realize through the activity chamber that the section of thick bamboo ring has the displacement space in each direction, effectively reduced the stress that the section of thick bamboo ring receives under the hot state, reduced the inefficacy risk, improved aeroengine's life greatly.
An aircraft characterised in that it comprises an aeroengine as described above.
In this scheme, adopt above-mentioned structural style, realize through the activity chamber that the section of thick bamboo ring has the displacement space in each direction, effectively reduced the stress that the section of thick bamboo ring receives under the hot state, reduced the inefficacy risk, improved the life of aircraft greatly.
On the basis of the common knowledge in the field, the above preferred conditions can be combined randomly to obtain the preferred embodiments of the invention.
The positive progress effects of the invention are as follows:
according to the ceramic matrix composite material flame tube connecting device, the aircraft engine and the aircraft, the bulge part limits the movement in the movable cavity, so that the cap cover realizes the axial and radial assembling and positioning of the tube ring through the buckle part, and the movable cavity realizes that the tube ring has displacement space in all directions, thereby effectively reducing the stress borne by the tube ring in a hot state, reducing the failure risk and greatly prolonging the service life.
Drawings
FIG. 1 is a schematic view of the internal structure of a ceramic matrix composite liner attachment in accordance with an embodiment of the present invention.
FIG. 2 is a schematic view of a portion of the internal structure of the ceramic matrix composite liner attachment of an embodiment of the present invention.
FIG. 3 is a schematic view of another portion of the internal structure of the ceramic matrix composite liner attachment of the present invention.
FIG. 4 is a schematic view of a portion of a snap member of the ceramic matrix composite liner attachment of an embodiment of the present invention.
Description of the reference numerals:
Convex part 11
Bulge section 21
Fastener member 3
Fastener 4
Detailed Description
The present invention will be more clearly and completely described below by way of examples and with reference to the accompanying drawings, but the present invention is not limited thereto.
As shown in fig. 1, fig. 2, fig. 3 and fig. 4, the cmc flame tube connecting device according to the embodiment of the present invention includes at least one tube ring 1, at least one cap 2 and a plurality of fastening members 3, one end of each of the plurality of fastening members 3 is connected to two sides of the cap 2 by a fastening member 4, the other end of each of the plurality of fastening members 3 extends outward and is bent in an opposite direction, so that a movable cavity 31 is formed between an end surface of the cap 2 and the plurality of fastening members 3, an end portion of the tube ring 1 has a protrusion 11 extending outward in a radial direction thereof, the movable cavity 31 is sleeved on the protrusion 11, so that the protrusion 11 moves in the movable cavity 31 and restricts the protrusion 11 from leaving the movable cavity 31, the material of the tube ring 1 is cmc.
The material of the cylinder ring 1 is ceramic matrix composite, and the rest parts such as the cap cover 2, the buckle part 3, the fastener 4 and the like are made of high-temperature alloy materials. One end of the buckle component 3 is mounted on the cap cover 2 through the fastener 4, the other end of the buckle component 3 extends outwards and forms a movable cavity 31 with the end face of the cap cover 2, and the fastener 4 is arranged in the movable cavity 31, so that the contact surface between the fastener 4 and the cap cover 2 and the buckle component 3 is large, and the connection is more stable. The barrel ring 1 is limited to move in the movable cavity 31 through the protruding part 11, so that the cap cover 2 can axially and radially assemble and position the barrel ring 1 through the buckle part 3, the barrel ring 1 can be displaced in all directions through the movable cavity 31, the stress on the barrel ring 1 is effectively reduced in a hot state, the failure risk is reduced, and the service life is greatly prolonged.
In this embodiment, the number of the cylinder rings 1 and the caps 2 is two, two caps 2 are respectively an outer cap and an inner cap, two cylinder rings 1 are respectively a flame tube outer ring and a flame tube inner ring, the outer cap is connected with the flame tube outer ring through a plurality of fastening components 3, and the inner cap is connected with the flame tube inner ring through a plurality of fastening components 3.
In the present embodiment, the boss 11 includes a first boss and a second boss, which are respectively located on both sides of the cylinder ring 1 and extend outward in opposite directions; the first boss and the second boss are movable in the movable chamber 31 in the axial direction, the radial direction, and the circumferential direction of the cylinder ring 1. The buckling parts 3 on the two sides of the cap 2 are bent along the opposite direction, the first protruding part and the second protruding part are respectively in clamping contact through the corresponding bending parts of the two buckling parts 3, the axial and radial freedom degrees of the cylinder ring 1 can be restrained, so that the cylinder ring 1 is axially and radially assembled and positioned, the protruding parts 11 are moved in the movable cavity 31 along the axial direction, the radial direction and the circumferential direction of the cylinder ring 1, the stress borne by the cylinder ring 1 is effectively reduced under a thermal state, the failure risk is reduced, and the service life of the ceramic matrix composite flame tube connecting device is greatly prolonged; meanwhile, the structure is simple, and the processing and the manufacturing are convenient. Wherein, the thickness of the first bulge and the second bulge in the cylinder ring 1 is larger than the thickness of other positions.
The ceramic matrix composite flame tube connecting device further comprises an elastic sealing ring 5, the elastic sealing ring 5 is located in the movable cavity 31, and the elastic sealing ring 5 is arranged between the buckle component 3 and the cylinder ring 1 in a pressing mode and exerts radial acting force on the buckle component 3 and the cylinder ring 1. The elastic sealing ring 5 has a certain radial pressing force during assembly, so that the buckle component 3 is in contact with the boss 11, the contact surface between the buckle component 3 and the boss 11 and the contact surface between the boss 11 and the elastic sealing ring 5 are in a pressing state, the sealing effect is achieved by using the elastic sealing ring 5, and the radial floating of the cylinder ring 1 can be realized. The cross section of the elastic sealing ring 5 may be U-shaped, or W-shaped, or other elastically deformable sealing members.
The end of the cap 2 is provided with a protruding section 21, the end of the cylinder ring 1 is provided with a groove 12, and the protruding section 21 is embedded in the groove 12 to realize the limiting effect along the circumferential direction of the cylinder ring 1. The protruding section 21 is embedded in the groove 12, and the metal arc-shaped protrusion can be used for circumferentially positioning the cylinder ring 1; meanwhile, the effect of curved surface sealing can be realized by metal expansion in a hot state, the contact area is increased by the convex section 21 and the groove 12, and the sealing performance is improved. Wherein, the surface shapes of the convex section 21 and the groove 12 are both arc-shaped, and the convex section 21 is in matched contact with the groove 12. The contact surface is large, and the sealing effect is further improved. The number of the convex sections 21 and the grooves 12 can be multiple, and the plurality of convex sections 21 and the plurality of grooves 12 are correspondingly arranged.
A plurality of snap members 3 are provided to the cap 2 continuously and uninterruptedly in the circumferential direction of the cap 2, and the snap members 3 are detachably attached to the cap 2 by bolts. The buckle part 3 can be designed into a plurality of sections in the circumferential direction, so that the buckle part 3 designed into a plurality of fan-shaped sections is wound into a circle, and the assembly is convenient; meanwhile, after the local damage, the invalid buckle component 3 can be replaced, so that the maintenance is convenient, and the maintenance cost is reduced.
In two adjacent buckle parts 3, one buckle part 3 has an outward extending protruding section 32, and the other buckle part 3 has an inward recessed avoiding section 33, and the protruding section 32 protrudes into the avoiding section 33 and abuts against the inner wall surface of the avoiding section 33. The protruding section 32 protrudes into the avoiding section 33, so that the contact area of two adjacent buckle parts 3 can be increased during assembly, and the matching degree is improved.
Wherein, a gap is arranged between the top end of the protruding section 32 and the groove bottom of the avoiding section 33. The buckle part 3 has a deformation displacement space through the gap when displacing in the circumferential direction, so that the stress borne by the buckle part 3 is effectively reduced in a thermal state, the failure risk is reduced, and the service life of the buckle part 3 is greatly prolonged.
The embodiment of the invention also discloses an aero-engine which comprises the ceramic matrix composite material flame tube connecting device. The barrel ring 1 is limited to move in the movable cavity 31 through the protruding portion 11, so that the cap cover 2 can be used for axially and radially assembling and positioning the barrel ring 1 through the buckle component 3, the barrel ring 1 can be displaced in all directions through the movable cavity 31, the stress borne by the barrel ring 1 is effectively reduced in a hot state, the failure risk is reduced, and the service life is greatly prolonged.
The embodiment of the invention also discloses an aircraft which comprises the aero-engine.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.
Claims (10)
1. The utility model provides a ceramic matrix composite flame tube connecting device, its characterized in that, it includes at least one section of thick bamboo ring, at least one cap and a plurality of buckle part, a plurality of buckle part's one end respectively through the fastener connect in the both sides of cap, a plurality of buckle part's the other end outwards extends and buckles along relative direction, so that the terminal surface and a plurality of cap be formed with movable chamber between the buckle part, the tip of section of thick bamboo ring has the bellying of outwards extending along its radial direction, movable chamber cover is located the bellying makes the bellying is in activity intracavity activity and restriction the bellying breaks away from movable chamber, the material of section of thick bamboo ring is ceramic matrix composite.
2. The ceramic matrix composite flame tube attachment of claim 1, wherein the boss includes a first boss and a second boss, the first boss and the second boss being located on opposite sides of the tube ring and extending outwardly in opposite directions, respectively;
the first boss and the second boss are movable in the axial direction, the radial direction, and the circumferential direction of the cylinder ring in the movable chamber.
3. The ceramic matrix composite liner connection assembly of claim 1, further comprising an elastomeric seal ring positioned within said movable cavity and compressed between and exerting a radial force on said snap member and said collar.
4. The ceramic matrix composite flameholder attachment of claim 1 wherein said cap has a protruding section at the end and said can ring has a groove at the end, said protruding section being embedded in said groove to provide a stop along the circumference of said can ring.
5. The ceramic matrix composite flameholder attachment of claim 4 wherein said raised section and said notch each have arcuate surfaces and said raised section matingly contacts said notch.
6. The ceramic matrix composite flame tube attachment of claim 1, wherein a plurality of said snap members are continuously and uninterruptedly disposed on said cap in a circumferential direction of said cap, and said snap members are detachably attached to said cap by bolts.
7. The ceramic matrix composite flameholder connection device according to claim 1, wherein one of said snap members has an outwardly extending protrusion section and the other of said snap members has an inwardly recessed relief section, and said protrusion section extends into said relief section and abuts against an inner wall surface of said relief section.
8. The ceramic matrix composite flameholder attachment of claim 7 wherein a gap is provided between a top end of said projecting section and a bottom of said relief section.
9. An aircraft engine, characterized in that it comprises a ceramic matrix composite liner attachment according to any one of claims 1 to 8.
10. An aircraft, characterized in that it comprises an aircraft engine according to claim 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110479983.1A CN115264536A (en) | 2021-04-30 | 2021-04-30 | Ceramic matrix composite flame tube connecting device, aircraft engine and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110479983.1A CN115264536A (en) | 2021-04-30 | 2021-04-30 | Ceramic matrix composite flame tube connecting device, aircraft engine and aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN115264536A true CN115264536A (en) | 2022-11-01 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110479983.1A Pending CN115264536A (en) | 2021-04-30 | 2021-04-30 | Ceramic matrix composite flame tube connecting device, aircraft engine and aircraft |
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| CN (1) | CN115264536A (en) |
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2021
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