CN114753894A - Ceramic matrix composite material runner structure - Google Patents
Ceramic matrix composite material runner structure Download PDFInfo
- Publication number
- CN114753894A CN114753894A CN202111342695.8A CN202111342695A CN114753894A CN 114753894 A CN114753894 A CN 114753894A CN 202111342695 A CN202111342695 A CN 202111342695A CN 114753894 A CN114753894 A CN 114753894A
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- CN
- China
- Prior art keywords
- ceramic matrix
- matrix composite
- runner
- ring
- whole
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 239000011153 ceramic matrix composite Substances 0.000 title claims abstract description 42
- 239000000463 material Substances 0.000 title description 16
- 238000009434 installation Methods 0.000 claims abstract description 25
- 238000003780 insertion Methods 0.000 claims abstract description 12
- 230000037431 insertion Effects 0.000 claims abstract description 12
- 238000006073 displacement reaction Methods 0.000 claims abstract description 4
- 239000000919 ceramic Substances 0.000 claims description 4
- 239000002131 composite material Substances 0.000 claims description 2
- 238000001816 cooling Methods 0.000 description 4
- 239000007769 metal material Substances 0.000 description 4
- 239000002184 metal Substances 0.000 description 3
- 206010066054 Dysmorphism Diseases 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 239000011159 matrix material Substances 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/005—Selecting particular materials
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/243—Flange connections; Bolting arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/20—Oxide or non-oxide ceramics
- F05D2300/22—Non-oxide ceramics
- F05D2300/226—Carbides
- F05D2300/2261—Carbides of silicon
Abstract
The application belongs to the field of aero-engine and gas turbine design, and particularly relates to a ceramic matrix composite runner structure. The ceramic matrix composite flow channel structure (1) comprises: the runner comprises a whole-ring runner main body, a front mounting edge and a rear mounting edge. The outer wall surface of the whole-ring runner main body is provided with a radial insertion groove, and the axial displacement of the whole-ring runner main body is limited by a radial insertion piece arranged in the radial insertion groove; the front mounting edge is arranged at the front end of the whole-ring runner main body, a special-shaped nut placing groove is formed in the front mounting edge, and the front mounting edge is connected with other ceramic matrix composite runner structures (2) through special-shaped nuts (4) and inner hexagon bolts (5); the back installation edge is arranged at the rear end of the whole-ring flow channel main body, a runway-shaped radial pin groove is uniformly formed in the whole-ring flow channel main body close to the back installation edge along the circumferential direction, and the back installation edge is matched with a bolt positioning pin (6) to be connected with the casing installation support ring (3).
Description
Technical Field
The application belongs to the field of aero-engine and gas turbine design, and particularly relates to a ceramic matrix composite runner structure.
Background
As shown in fig. 1-3, in the design of the turbine rear runner casing of modern aircraft engines and gas turbines, a runner plate structure made of high-temperature alloy material is generally adopted, and cooling air (generally compressor bleed air or outer duct bleed low-temperature air) needs to be introduced for cooling.
The existing structure is a metal material structure, the temperature resistance is low, the maximum use temperature is about 1250K, and the use state of the engine is limited; the existing structure is a metal material structure, and a large amount of air compressors or external ducts are needed for air entraining, so that the cycle efficiency of the engine is reduced; with the increase of the front temperature of the turbine of the aircraft engine, the metal material structure gradually exposes the problems of local overtemperature, uncoordinated thermal deformation and the like.
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 application aims to provide a ceramic matrix composite material flow channel structure so as to solve at least one problem existing in the prior art.
The technical scheme of the application is as follows:
a ceramic matrix composite flow channel structure, comprising:
the outer wall surface of the whole-ring flow channel main body is provided with a radial insertion groove, and the axial displacement of the whole-ring flow channel main body is limited by a radial insertion piece arranged in the radial insertion groove;
the front mounting edge is arranged at the front end of the whole-ring runner main body, a special-shaped nut placing groove is formed in the front mounting edge, and the front mounting edge is connected with other ceramic matrix composite runner structures through special-shaped nuts and inner hexagon bolts;
the back installation limit, the setting of back installation limit is in the rear end of whole ring runner main part is close to back installation limit department the radial cotter way of runway type has evenly been seted up along circumference in the whole ring runner main part, back installation limit cooperation bolt locating pin is connected with machine casket installation support ring.
In at least one embodiment of the present application, the ceramic matrix composite flow channel structure is a SiC ceramic matrix composite.
In at least one embodiment of this application, the dysmorphism nut standing groove is the ladder groove.
In at least one embodiment of the present application, the special-shaped nut includes cylindrical sections at both ends and a special-shaped section at a middle portion, and when assembled, the cylindrical section at one end and the special-shaped section at the middle portion are accommodated in the special-shaped nut placement groove.
In at least one embodiment of the present application, the profiled section is rectangular.
In at least one embodiment of this application, cartridge receiver installation support ring have with the joint portion of back installation limit looks adaptation to and set up the connecting portion of radial bolt hole, cartridge receiver installation support ring passes through joint portion joint and is in back installation edge, through the bolt locating pin will the connecting portion of cartridge receiver installation support ring with the radial cotter way of race type on the whole ring runner main part is connected.
The invention has at least the following beneficial technical effects:
the application relates to a ceramic matrix composite material flow passage structure.
Drawings
FIG. 1 is a schematic representation of a prior art turbine aft flowpath configuration;
FIG. 2 is a view in the direction A of FIG. 1;
FIG. 3 is a view B-B of FIG. 2;
FIG. 4 is a schematic view of the overall assembly of a ceramic matrix composite flow channel structure according to an embodiment of the present application;
FIG. 5 is a schematic view of a ceramic matrix composite flow channel according to an embodiment of the present application;
FIG. 6 is a schematic view of another embodiment of a ceramic matrix composite flow channel in accordance with the present application;
FIG. 7 is a schematic view of a profile nut according to an embodiment of the present application;
FIG. 8 is a side view of FIG. 7;
FIG. 9 is a schematic view of a socket head cap screw according to an embodiment of the present application;
FIG. 10 is a side view of FIG. 9;
FIG. 11 is a schematic view of a casing mounting support ring according to an embodiment of the present application;
FIG. 12 is a side view of FIG. 11;
FIG. 13 is a schematic view of a bolt alignment pin according to one embodiment of the present application.
Wherein:
1-ceramic matrix composite material flow passage structure; 2-other ceramic matrix composite material flow passage structures; 3, mounting a support ring on the casing; 4-special-shaped nuts; 5-hexagon socket head cap screw; 6-bolt positioning pin.
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 obtained by a person of ordinary skill in the art based on the embodiments in the present application without making any creative effort belong to 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 "central," "longitudinal," "lateral," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in the orientations and positional relationships indicated in the drawings, which are based on the orientation or positional relationship shown in the drawings, and are used for convenience in describing the present application and for simplicity in description, but do not indicate or imply that the devices or elements referred to 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 will be described in further detail with reference to fig. 4 to 13.
The application provides a ceramic matrix combined material runner structure, this ceramic matrix combined material runner structure 1 includes: the runner comprises a whole-ring runner main body, a front mounting edge and a rear mounting edge.
As shown in fig. 4-5, the ceramic matrix composite runner structure 1 is an integral ring casing structure, a radial insertion groove is formed on an outer wall surface of the integral ring runner body, and the axial displacement of the integral ring runner body can be limited by a radial insertion piece arranged in the radial insertion groove; the front mounting edge is arranged at the front end of the whole-ring runner main body, a special-shaped nut placing groove is formed in the front mounting edge, and the front mounting edge can be connected with other ceramic matrix composite runner structures 2 through a special-shaped nut 4 and an inner hexagon bolt 5; the rear mounting edge is arranged at the rear end of the whole-ring flow channel main body, runway-shaped radial pin grooves are uniformly formed in the whole-ring flow channel main body close to the rear mounting edge along the circumferential direction, and the rear mounting edge is connected with the casing mounting support ring 3 through the bolt positioning pin 6.
In the preferred embodiment of the application, the ceramic matrix composite runner structure 1 is a SiC ceramic matrix composite, which increases the temperature resistance and sealing capability of the runner. The casing mounting support ring 3, the special-shaped nut 4, the inner hexagon bolt 5 and the bolt positioning pin 6 are all made of metal materials.
As shown in fig. 6, the other ceramic matrix composite flow channel structure 2 is provided with bolt holes thereon for connecting with the other ceramic matrix composite flow channel structure 1.
In the preferred embodiment of this application, the dysmorphism nut standing groove is the ladder groove. As shown in fig. 7 to 8, the modified nut 4 is provided with an internal thread, and the modified nut 4 includes cylindrical sections 41 at both ends and a modified section 42 in the middle, and when assembled, the cylindrical section 41 at one end and the modified section 42 in the middle are accommodated in the modified nut accommodating groove. The profiled section 42 in the middle of the profiled nut 4 is rectangular or other suitable shape with a large bearing area.
In the preferred embodiment of the present application, the socket head cap screw 5 has a large bearing area for engaging with the profile nut 4 to secure the cmc casing as shown in fig. 9-10. Through the cooperation of special-shaped nut 4 and hexagon socket head cap screw 5, can realize the connection between ceramic matrix composite casing, have big bearing area bolted connection structure, and special-shaped nut 4 has from the limit function.
In the preferred embodiment of the present application, the structure of the casing installation support ring 3 is as shown in fig. 11-12, which is a segmented structure uniformly distributed circumferentially, the casing installation support ring 3 has a clamping portion adapted to the rear installation edge and a connecting portion provided with radial bolt holes, the casing installation support ring 3 is radially clamped inward on the rear installation edge by the clamping portion, and the connecting portion of the casing installation support ring 3 is connected with the runner-type radial pin slot on the whole-ring runner body by the bolt positioning pin 6, so that the connection of the ceramic matrix composite casing and the metal casing can be realized, and the thermal deformation coordination capability of runners made of different materials can be enhanced.
In this embodiment, the bolt positioning pin 6 is structured as shown in fig. 13, and a screw portion thereof is provided with a thread section and a pin section, the thread section is used for connecting with a radial bolt hole of a connecting portion of the casing mounting support ring 3, and the pin section is used for connecting with a runway-type radial pin groove of the whole ring runner body.
According to the ceramic matrix composite material runner structure, when the ceramic matrix composite material runner structure works, the ceramic matrix composite material runner structure 1 made of the SiC ceramic matrix composite material is directly contacted with high-temperature fuel gas, the ceramic matrix composite material runner structure can be used in a working environment of over 1700K, and the runner structure capacity is greatly improved; the special-shaped nuts 4 and the inner hexagon bolts 5 with large bearing areas are used among the runners of the SiC ceramic matrix composite, so that the actual bearing area of the mounting surface of the casing is increased, the actual stress of the mounting surface of the runner of the composite material is reduced, the safety is improved, and the service life is prolonged; when the runner structure and the mounting casing are deformed relatively, the runway-type radial pin groove and the bolt positioning pin 6 structure can realize radial and axial relative sliding movement, and the problem of incongruity of thermal deformation of the high-temperature runner and the low-temperature mounting support ring is solved.
According to the ceramic matrix composite material runner structure, the metal structure is changed into the ceramic matrix composite material, so that the temperature resistance of the structure is improved by over 400K; cooling air is reduced, and loss caused by cooling the air compressor and external contained air is reduced; the structure is provided with the bolt positioning pin, the runway-type radial pin slot and other structures, so that the problem of incongruity of thermal deformation of the ceramic base and metal can be adapted, and the structural safety is improved.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (6)
1. A ceramic matrix composite flow channel structure, characterized in that the ceramic matrix composite flow channel structure (1) comprises:
the outer wall surface of the whole-ring flow channel main body is provided with a radial insertion groove, and the axial displacement of the whole-ring flow channel main body is limited by a radial insertion piece arranged in the radial insertion groove;
the front mounting edge is arranged at the front end of the whole-ring runner main body, a special-shaped nut placing groove is formed in the front mounting edge, and the front mounting edge is connected with other ceramic-based composite runner structures (2) through special-shaped nuts (4) and inner hexagon bolts (5);
the back installation limit, the back installation limit sets up the rear end of whole ring runner main part is close to back installation limit department the whole ring runner main part is gone up along circumference and has evenly seted up the radial cotter way of runway type, back installation limit cooperation bolt locating pin (6) are connected with receiver installation support ring (3).
2. The ceramic matrix composite flow channel structure according to claim 1, wherein the ceramic matrix composite flow channel structure (1) is a SiC ceramic matrix composite.
3. The ceramic matrix composite flow channel structure of claim 1, wherein said contoured nut receiving slot is a stepped slot.
4. The ceramic matrix composite flow channel structure according to claim 3, wherein the special-shaped nut (4) comprises cylindrical sections (41) at both ends and a special-shaped section (42) in the middle, and when assembled, the cylindrical section (41) at one end and the special-shaped section (42) in the middle are accommodated in the special-shaped nut accommodating groove.
5. The ceramic matrix composite flow channel structure of claim 4, wherein said profiled section (42) is rectangular.
6. The ceramic matrix composite runner structure according to claim 1, wherein the casing mounting support ring (3) has a clamping portion adapted to the rear mounting edge and a connecting portion with radial bolt holes, the casing mounting support ring (3) is clamped to the rear mounting edge by the clamping portion, and the connecting portion of the casing mounting support ring (3) is connected to the runner type radial pin groove of the whole-ring runner body by the bolt positioning pin (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111342695.8A CN114753894A (en) | 2021-11-12 | 2021-11-12 | Ceramic matrix composite material runner structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111342695.8A CN114753894A (en) | 2021-11-12 | 2021-11-12 | Ceramic matrix composite material runner structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114753894A true CN114753894A (en) | 2022-07-15 |
Family
ID=82325342
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111342695.8A Pending CN114753894A (en) | 2021-11-12 | 2021-11-12 | Ceramic matrix composite material runner structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN114753894A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115614173A (en) * | 2022-12-19 | 2023-01-17 | 中国航发沈阳发动机研究所 | Radial overlap joint axial grafting inner cone installation limit structure |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4522559A (en) * | 1982-02-19 | 1985-06-11 | General Electric Company | Compressor casing |
| CN201593548U (en) * | 2009-11-12 | 2010-09-29 | 长安大学 | Bolt type anti-theft nut and special wrench thereof |
| US20130202430A1 (en) * | 2012-02-06 | 2013-08-08 | Snecma | Gas turbine engine fan casing having a flange for fastening pieces of equipment |
| CN204921574U (en) * | 2015-07-14 | 2015-12-30 | 东莞市德尔能新能源股份有限公司 | Protection shield and plastic part locking structure |
| CN107882599A (en) * | 2017-11-01 | 2018-04-06 | 中国航发湖南动力机械研究所 | Monoblock type turbine outer ring attachment structure and turbogenerator |
| CN209458041U (en) * | 2019-01-31 | 2019-10-01 | 中国航发商用航空发动机有限责任公司 | Connection structure and tail spray component |
| CN112576320A (en) * | 2020-12-07 | 2021-03-30 | 中国航发沈阳发动机研究所 | Air guide sleeve structure capable of coordinating cold and hot state deformation |
| US20210148248A1 (en) * | 2019-11-19 | 2021-05-20 | Rolls-Royce North American Technologies Inc. | Turbine shroud assembly with flange mounted ceramic matrix composite turbine shroud ring |
-
2021
- 2021-11-12 CN CN202111342695.8A patent/CN114753894A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4522559A (en) * | 1982-02-19 | 1985-06-11 | General Electric Company | Compressor casing |
| CN201593548U (en) * | 2009-11-12 | 2010-09-29 | 长安大学 | Bolt type anti-theft nut and special wrench thereof |
| US20130202430A1 (en) * | 2012-02-06 | 2013-08-08 | Snecma | Gas turbine engine fan casing having a flange for fastening pieces of equipment |
| CN204921574U (en) * | 2015-07-14 | 2015-12-30 | 东莞市德尔能新能源股份有限公司 | Protection shield and plastic part locking structure |
| CN107882599A (en) * | 2017-11-01 | 2018-04-06 | 中国航发湖南动力机械研究所 | Monoblock type turbine outer ring attachment structure and turbogenerator |
| CN209458041U (en) * | 2019-01-31 | 2019-10-01 | 中国航发商用航空发动机有限责任公司 | Connection structure and tail spray component |
| US20210148248A1 (en) * | 2019-11-19 | 2021-05-20 | Rolls-Royce North American Technologies Inc. | Turbine shroud assembly with flange mounted ceramic matrix composite turbine shroud ring |
| CN112576320A (en) * | 2020-12-07 | 2021-03-30 | 中国航发沈阳发动机研究所 | Air guide sleeve structure capable of coordinating cold and hot state deformation |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115614173A (en) * | 2022-12-19 | 2023-01-17 | 中国航发沈阳发动机研究所 | Radial overlap joint axial grafting inner cone installation limit structure |
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