CN115126557A - Mounting flange structure for connecting casings of gas turbine engines and mounting method - Google Patents
Mounting flange structure for connecting casings of gas turbine engines and mounting method Download PDFInfo
- Publication number
- CN115126557A CN115126557A CN202210893120.3A CN202210893120A CN115126557A CN 115126557 A CN115126557 A CN 115126557A CN 202210893120 A CN202210893120 A CN 202210893120A CN 115126557 A CN115126557 A CN 115126557A
- Authority
- CN
- China
- Prior art keywords
- mounting
- casing
- casings
- gas turbine
- buckles
- 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
Images
Classifications
-
- 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
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
Abstract
The invention discloses a mounting flange structure and a mounting method for connecting casings of a gas turbine engine, wherein a plurality of buckles are fixedly arranged on the mounting edges of two casings respectively at uniform intervals along the circumferential direction, when the mounting flange structure is assembled, only one circle of buckles on the mounting edge of one casing and one circle of buckles on the mounting edge of the other casing are required to be sequentially staggered in the circumferential direction, a circumferential mounting channel is formed between the two circles of buckles, a hoop is mounted in the mounting channel and locked through a locking piece, and the mounting edges of the two casings can be tightly attached, so that the axial connection of the two casings is realized. The quick connection and the disassembly of the casings can be very convenient, the casings can be quickly connected and disassembled, the clamp is clamped in the two circles of buckles to form in the circumferential installation channel, the two casings can be reliably axially connected, the installation edges of the two casings are tightly attached, and the air leakage phenomenon of the joint of the two installation edges can be effectively reduced.
Description
Technical Field
The invention relates to the technical field of gas turbine engines, in particular to a mounting flange structure for connecting a casing of a gas turbine engine.
Background
In the field of gas turbine engines, the inner and outer casings of the engine are generally divided into multiple sections, such as a compressor casing, a combustor casing, a turbine casing, a reducer casing and the like, and the casings have the functions of containing a flow passage, transmitting axial force and torque and the like. The existing casings are axially connected through bolts and nuts, specifically, the casings are provided with mounting edges at connecting ends, a large number of through holes are formed in the mounting edges along the circumferential direction, the through holes in the mounting edges of two adjacent casings correspond to each other in pairs, and the bolts penetrate through the through holes to be matched with the nuts to fix the two mounting edges together.
However, the existing screw and nut fastening structure is time-consuming to assemble and disassemble, and tens of screw and nuts are generally arranged on the mounting edge along the circumferential direction in order to realize fastening reliable connection. The more the number of the screws and the nuts is, the more reliable the fastening is, but the more time is consumed for dismounting. In addition, if the working temperature of the mounting edge is high, for example, the mounting edge of the combustion chamber casing has high temperature, the screw and the nut are easy to be adhered, and the difficulty and the time consumption of decomposition are higher. When an engine part or a complete machine is tested, tasks of multiple schemes and multiple engine parts are often required to be completed, the quantity of dismounting tasks is large, time consumption is serious, and test task nodes are affected. Moreover, quick disassembly and assembly cannot be realized when the engine has unexpected faults and needs to be disassembled for inspection. In addition, the area fastening force between adjacent screws is unevenly distributed, and the air leakage phenomenon is easily generated.
Disclosure of Invention
The invention provides a mounting flange structure for connecting a casing of a gas turbine engine, which aims to solve the technical problem that the existing casing of the gas turbine engine is inconvenient to assemble and disassemble due to the fact that the casing is connected through screws and nuts.
According to one aspect of the invention, a mounting flange structure for connecting casings of gas turbine engines is provided, which comprises buckles, a hoop and a locking piece, wherein the buckles are fixedly arranged on a mounting edge of a first casing and a mounting edge of a second casing at uniform intervals along the circumferential direction, when the first casing and the second casing are assembled, a circle of buckles on the mounting edge of the first casing and a circle of buckles on the mounting edge of the second casing are sequentially staggered from each other in the circumferential direction, a circumferential mounting channel is formed between the two circles of buckles, and the hoop is arranged in the mounting channel and is locked by the locking piece, so that the mounting edge of the first casing and the mounting edge of the second casing are tightly attached.
Furthermore, the buckle is a rotating body sector section with a Z-shaped section, and a rotating shaft of the rotating body sector section is overlapped with a theoretical axis of the casing.
Further, the buckle includes first working face, second working face and third working face, the laminating of the outside plane on first working face and installation limit, the laminating of the outside cylinder on second working face and installation limit, the third working face with the location working face laminating of clamp both sides.
Furthermore, the first working face is a plane, the second working face is a cylindrical face, the third working face is a conical face, and the taper is the same as the taper of the positioning working faces on the two sides of the hoop.
Furthermore, the circumferential gaps between the adjacent buckles on the two mounting edges are the same, the angles of the adjacent buckles which are mutually separated in the circumferential direction are the same as the fan-shaped angles of the buckles, and when the two casings are assembled, the buckle on the mounting edge on one side is just clamped between the two adjacent buckles on the mounting edge on the other side, so that the circumferential positioning of the two mounting edges is realized.
Furthermore, the two mounting edges are circumferentially positioned through positioning pins or positioning grooves.
Furthermore, the quantity of clamp is at least two, be equipped with the tongue on the clamp, the through-hole has been seted up on the tongue, locks through the retaining member between two adjacent clamps, at least two cover 360 regions of circumference after locking each other.
Further, the number of the clamping bands is 2, and each clamping band covers a 180-degree area in the circumferential direction.
In addition, the invention also provides a mounting method for connecting the casing of the gas turbine engine, which adopts the mounting flange structure and comprises the following steps:
a plurality of buckles are respectively and fixedly arranged on the mounting edge of the first casing and the mounting edge of the second casing at equal intervals along the circumferential direction;
matching the first casing with the second casing to ensure that a circle of buckles on the mounting edge of the first casing and a circle of buckles on the mounting edge of the second casing are sequentially staggered from each other in the circumferential direction, and forming a circumferential mounting channel between the two circles of buckles;
and installing the clamp in the circumferential installation channel and locking the clamp by using a locking piece to ensure that the installation edge of the first casing is tightly attached to the installation edge of the second casing.
Further, when the first casing and the second casing are matched, the buckle on the mounting edge on one side is just clamped between two adjacent buckles on the mounting edge on the other side, so that the circumferential positioning of the two mounting edges is realized, and a circumferential mounting channel is formed between the third working faces of the two circles of buckles.
The invention has the following effects:
according to the mounting flange structure for connecting the casings of the gas turbine engine, a plurality of buckles are fixedly arranged on the mounting edges of the two casings at equal intervals along the circumferential direction, when the mounting flange structure is assembled, only one circle of buckles on the mounting edge of one casing and one circle of buckles on the mounting edge of the other casing are required to be staggered in sequence along the circumferential direction, a circumferential mounting channel is formed between the two circles of buckles, a hoop is mounted in the mounting channel and locked through a locking piece, the mounting edges of the two casings can be tightly attached, and therefore the axial connection of the two casings is achieved. And when two machine casket were dismantled to needs, only need loosen the retaining member on the clamp, take out the clamp from the mounting groove way, can separate two machine casket. The mounting flange structure for connecting the casings of the gas turbine engine is very convenient to assemble and disassemble, can realize quick connection and disassembly of the casings, is clamped in the two circles of buckles to form in the circumferential mounting channel, can realize reliable axial connection of the two casings, simultaneously enables the mounting edges of the two casings to be tightly attached, can effectively reduce the air leakage phenomenon at the joint of the two mounting edges, is particularly suitable for the test casing of the aviation turboshaft engine, can greatly shorten the time consumed by assembling and disassembling a test piece, reduces the assembling and disassembling difficulty, shortens the test preparation time, and reduces the air leakage at the mounting edges.
In addition, the installation method for gas turbine engine case attachment of the present invention also has the advantages described above.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic perspective view of a buckle according to a preferred embodiment of the present invention.
Fig. 2 is a front view of the buckle according to the preferred embodiment of the present invention.
Fig. 3 is a left side view of the buckle according to the preferred embodiment of the present invention.
Fig. 4 is a schematic view of the structure of a clip according to a preferred embodiment of the present invention.
FIG. 5 is a partial view of a clip according to the preferred embodiment of the present invention showing a through hole in the tab.
Fig. 6 is a partial structural view illustrating the snap-fit fastening of the preferred embodiment of the present invention to the mounting edge of the first casing.
Fig. 7 is a schematic view of the clip of the preferred embodiment of the present invention engaging a catch on the mounting edge of the first casing.
Fig. 8 is a schematic view of the clip of the preferred embodiment of the present invention engaging a catch on the mounting edge of the second casing.
Fig. 9 is a schematic view of the configuration of the preferred embodiment of the present invention in which a circumferential mounting channel is formed between the third running surfaces of the two rings of snaps.
Fig. 10 is a schematic view of the preferred embodiment of the invention showing the clip locked in the circumferential mounting channel by the retaining member.
FIG. 11 is a partial schematic structural view of a mounting flange configuration for gas turbine engine case attachment in accordance with a preferred embodiment of the present invention.
Description of the reference numerals
1. Buckling; 2. clamping a hoop; 3. a mounting edge of the first case; 4. a mounting edge of the second case; 5. a locking member; 101. a first working surface; 102. a second working surface; 103. a third working surface; 301. an outer plane; 302. an outer cylindrical surface; 201. a tongue; 202. a through hole; 203. and positioning the working surface.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the drawings, but the invention can be practiced in many different ways, which are defined and covered by the following.
As shown in fig. 1 to 11, a preferred embodiment of the present invention provides a mounting flange structure for connecting casings of gas turbine engines, which includes fasteners 1, a clip 2 and a locking member 5, wherein the fasteners 1 are fixedly mounted on a mounting edge 3 of a first casing and a mounting edge 4 of a second casing at uniform intervals along a circumferential direction, when the first casing is assembled with the second casing, a circle of the fasteners 1 on the mounting edge 3 of the first casing and a circle of the fasteners 1 on the mounting edge 4 of the second casing are sequentially staggered from each other in the circumferential direction, and a circumferential mounting channel is formed between the two circles of the fasteners 1, and the clip 2 is mounted in the mounting channel and locked by the locking member 5, so that the mounting edge 3 of the first casing and the mounting edge 4 of the second casing are tightly attached. And when first machine casket and second machine casket are disassembled to needs, only need loosen retaining member 5, then take out clamp 2, can realize first machine casket and second machine casket mutual separation. The locking piece 5 is locked by matching a screw and a nut or locking a bolt and a nut.
It can be understood that the mounting flange structure for gas turbine engine case connection of this embodiment, through respectively at the installation edge of two casings along the fixed a plurality of buckles 1 that set up of even interval of circumference, when assembling, only need to stagger each other in proper order in circumference with round buckle 1 on one of them casing installation edge and round buckle 1 on another casing installation edge, and form the installation channel of circumference between two circles of buckles 1, install clamp 2 in this installation channel and through retaining member 5 locking, can closely laminate the installation edge of two casings, thereby realize the axial connection of two casings. And when two casings need to be dismantled, only need loosen retaining member 5 on the clamp 2, take out clamp 2 from the mounting channel, can separate two casings. The mounting flange structure for connecting the casings of the gas turbine engine is very convenient to assemble and disassemble, can realize quick connection and disassembly of the casings, can realize reliable axial connection of the two casings by clamping the hoop 2 in the two circles of buckles 1 formed in the circumferential mounting channel, can make the mounting edges of the two casings tightly attached, can effectively reduce the air leakage phenomenon at the joint of the two mounting edges, is particularly suitable for the test casing of the aviation turboshaft engine, can greatly shorten the time consumed by assembling and disassembling a test piece, reduces the assembling and disassembling difficulty, shortens the test preparation time and reduces the air leakage of the mounting edges.
Optionally, the buckle 1 is a rotating body sector section with a Z-shaped cross section, a rotating shaft of the rotating body sector section coincides with a theoretical axis of the casing, and the buckle 1 can be fixedly mounted on the mounting edge by welding, bolting, riveting or the like. Specifically, buckle 1 includes first working face 101, second working face 102 and third working face 103, the laminating of the outside plane 301 of first working face 101 and installation limit, the laminating of the outside cylinder 302 of second working face 102 and installation limit, third working face 103 with the laminating of the location working face 203 of clamp 2 both sides. The first working surface 101 is a plane, the second working surface 102 is a cylindrical surface, and the third working surface 103 is a conical surface, and the taper is the same as the taper of the positioning working surfaces 203 on both sides of the band 2. The second working surface 102 of the buckle 1 covers the mounting edge and is attached to the outer cylindrical surface 302, so that the air leakage of the mounting edge along the radial direction can be effectively reduced.
It will be appreciated that the clamp 2 is a sector of a body of revolution having a mouth-shaped cross-section. Optionally, the number of the hoop 2 is at least two, a tongue 201 is arranged on the hoop 2, a through hole 202 is formed in the tongue 201, two adjacent hoops 2 are locked by a locking member 5, and at least two hoops 2 cover a circumferential 360-degree area after being locked with each other, so that the locking force is uniformly distributed. The number of the clamping bands 2 is n, and each clamping band 2 covers a circumferential 360 DEG/n area. Preferably, the number of clamping bands 2 is 2, each clamping band 2 covering a 180 ° area in the circumferential direction.
It can be understood that the circumferential clearance between the adjacent buckles 1 on the two mounting edges is the same, and the angles of the adjacent buckles 1 which are separated from each other in the circumferential direction are the same as the sector angle alpha of the buckle 1, when the two casings are assembled, the buckle 1 on the mounting edge on one side is just clamped between the two adjacent buckles 1 on the mounting edge on the other side, and therefore the circumferential positioning of the two mounting edges can be realized through the mutual dislocation matching of the two rows of buckles 1. Optionally, the two mounting edges can be circumferentially positioned through positioning pins or positioning grooves, so that the reliability of circumferential positioning is improved. After the two casings are assembled, a circumferential installation channel is formed between the third working faces 103 of the buckles 1 on different installation edges, the hoop 2 is installed in the installation channel, the positioning working faces 203 on two sides of the hoop 2 are respectively attached to the third working faces 103 of the buckles 1 on the installation edges on the two sides, then the locking piece 5 is locked, under the locking action of the locking piece 5, the hoop 2 tends to contract inwards along the radial direction, and then the two installation edges are extruded to move backwards, so that the two installation edges move oppositely and are closely attached together. For example, as shown in fig. 10, the circle of the buckle 1 on the mounting edge 3 of the first casing moves to the left under the pressing action of the clamping band 2, the circle of the buckle 1 on the mounting edge 4 of the second casing moves to the right under the pressing action of the clamping band 2, so that the mounting edge 3 of the first casing moves to the right, the mounting edge 4 of the second casing moves to the left, and finally the two mounting edges are tightly attached together.
In addition, another embodiment of the present invention provides a mounting method for a gas turbine engine case connection, preferably using a mounting flange structure as described above, comprising the following:
a plurality of buckles 1 are respectively and fixedly arranged on the mounting edge 3 of the first casing and the mounting edge 4 of the second casing at equal intervals along the circumferential direction;
matching the first casing with the second casing to ensure that the circle of buckles 1 on the mounting edge 3 of the first casing and the circle of buckles 1 on the mounting edge 4 of the second casing are sequentially staggered from each other in the circumferential direction, and forming a circumferential mounting channel between the two circles of buckles 1;
and (3) installing the hoop 2 in the circumferential installation channel and locking the hoop 2 by using a locking piece 5 to ensure that the installation edge 3 of the first casing is tightly attached to the installation edge 4 of the second casing.
It can be understood that, in the installation method for connecting the casings of the gas turbine engine of the embodiment, the plurality of buckles 1 are fixedly arranged on the installation edges of the two casings respectively at uniform intervals along the circumferential direction, when the two casings are assembled, only one circle of buckle 1 on the installation edge of one of the casings and one circle of buckle 1 on the installation edge of the other casing are required to be staggered in sequence along the circumferential direction, a circumferential installation channel is formed between the two circles of buckles 1, the hoop 2 is installed in the installation channel and locked through the locking piece 5, the installation edges of the two casings can be tightly attached, and therefore the axial connection of the two casings is achieved. And when two casings need to be dismantled, only need loosen retaining member 5 on the clamp 2, take out clamp 2 from the mounting channel, can separate two casings. The installation method for connecting the casings of the gas turbine engine can realize quick connection and disassembly of the casings, and the hoop 2 is clamped in the two circles of buckles 1 to form the two casings in the circumferential installation channel, so that reliable axial connection of the two casings can be realized, and meanwhile, the installation edges of the two casings are tightly attached, so that the air leakage phenomenon at the joint of the two installation edges can be effectively reduced.
It can be understood that when the first casing and the second casing are matched, the buckle 1 on the mounting edge on one side is just clamped between two adjacent buckles 1 on the mounting edge on the other side, so that the circumferential positioning of the two mounting edges is realized, and a circumferential mounting channel is formed between the third working surfaces 103 of the two circles of buckles 1.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. The utility model provides a mounting flange structure for gas turbine engine machine casket is connected, a serial communication port, including buckle (1), clamp (2) and retaining member (5), buckle (1) are along the even interval fixed mounting in circumference on the installation limit (3) of first machine casket and the installation limit (4) of second machine casket, when first machine casket and second machine casket were assembled, round buckle (1) on the installation limit (3) of first machine casket and round buckle (1) on the installation limit (4) of second machine casket stagger each other in proper order in circumference to form the installation channel of circumference between two circles buckle (1), install clamp (2) install in the installation channel and through retaining member (5) locking, so that the installation limit (3) of first machine casket and the installation limit (4) of second machine casket closely laminate.
2. A mounting flange structure for a gas turbine engine casing connection according to claim 1, characterized in that said snap (1) is a sector of a body of revolution with a Z-shaped section, the rotation axis of which coincides with the theoretical axis of the casing.
3. A mounting flange structure for a gas turbine engine casing connection according to claim 2, characterized in that the clip (1) comprises a first working surface (101), a second working surface (102) and a third working surface (103), the first working surface (101) being attached to the outer plane (301) of the mounting edge, the second working surface (102) being attached to the outer cylindrical surface (302) of the mounting edge, and the third working surface (103) being attached to the positioning working surfaces (203) on both sides of the band (2).
4. A mounting flange structure for a gas turbine engine casing connection according to claim 3, characterized in that the first working surface (101) is a plane surface, the second working surface (102) is a cylindrical surface, the third working surface (103) is a conical surface, and the conicity is the same as the conicity of the positioning working surfaces (203) on both sides of the band (2).
5. A mounting flange structure for a connection of casings of gas turbine engines according to claim 2, characterized in that the circumferential clearances between adjacent clips (1) on both mounting edges are the same, and the adjacent clips (1) are circumferentially spaced from each other by the same angle as the fan angle of the clips (1), so that when two casings are assembled, the clips (1) on one mounting edge are just caught between the adjacent two clips (1) on the other mounting edge, thereby achieving the circumferential positioning of both mounting edges.
6. A mounting flange structure for a gas turbine engine case connection according to claim 5, wherein both mounting edges are also circumferentially positioned by locating pins or slots.
7. The mounting flange structure for the connection of the casing of the gas turbine engine as set forth in claim 1, characterized in that the number of the clamping bands (2) is at least two, the clamping bands (2) are provided with a tongue (201), the tongue (201) is provided with a through hole (202), two adjacent clamping bands (2) are locked by a locking member (5), and at least two clamping bands (2) cover a circumferential 360-degree area after being locked with each other.
8. A mounting flange structure for a gas turbine engine casing connection according to claim 7, characterized in that the number of clips (2) is 2, each clip (2) covering a 180 ° area in the circumferential direction.
9. A mounting flange structure according to any one of claims 1 to 8, used in a mounting method for a gas turbine engine casing connection, comprising:
a plurality of buckles (1) are respectively and fixedly arranged on the mounting edge (3) of the first casing and the mounting edge (4) of the second casing at equal intervals along the circumferential direction;
the first casing and the second casing are matched, so that a circle of buckles (1) on the mounting edge (3) of the first casing and a circle of buckles (1) on the mounting edge (4) of the second casing are sequentially staggered from each other in the circumferential direction, and a circumferential mounting channel is formed between the two circles of buckles (1);
the hoop (2) is installed in the circumferential installation channel, the hoop (2) is locked by the locking piece (5), and the installation edge (3) of the first casing is tightly attached to the installation edge (4) of the second casing.
10. The mounting method for a gas turbine engine casing connection according to claim 9, characterized in that, when the first casing is mated with the second casing, the catch (1) on the mounting edge on one side is just caught between two adjacent catches (1) on the mounting edge on the other side to achieve circumferential positioning of the two mounting edges and to form a circumferential mounting channel between the third running surfaces (103) of the two rings of catches (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210893120.3A CN115126557A (en) | 2022-07-27 | 2022-07-27 | Mounting flange structure for connecting casings of gas turbine engines and mounting method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210893120.3A CN115126557A (en) | 2022-07-27 | 2022-07-27 | Mounting flange structure for connecting casings of gas turbine engines and mounting method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115126557A true CN115126557A (en) | 2022-09-30 |
Family
ID=83386143
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210893120.3A Pending CN115126557A (en) | 2022-07-27 | 2022-07-27 | Mounting flange structure for connecting casings of gas turbine engines and mounting method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115126557A (en) |
-
2022
- 2022-07-27 CN CN202210893120.3A patent/CN115126557A/en active Pending
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US5052891A (en) | Connection for gas turbine engine rotor elements | |
| US7364402B2 (en) | Turbine module for a gas turbine engine | |
| US9458726B2 (en) | Dovetail retention system for blade tracks | |
| RU2436965C2 (en) | Device for attachment of guide vanes of turbine, turbine and aircraft engine with such equipment | |
| US9039351B2 (en) | Annular flange for fastening a rotor or stator element | |
| KR101779146B1 (en) | Inter stage seal housing having a replaceable wear strip | |
| WO2014099097A2 (en) | Combustor seal mistake-proofing for a gas turbine engine | |
| EP3273013B1 (en) | Assembly for a turbine engine | |
| CA2935993C (en) | Spoke locking architecture | |
| CA2857817C (en) | Fastening system for rotor hubs | |
| US8087252B2 (en) | Turbomachine combustion chamber | |
| CN115126557A (en) | Mounting flange structure for connecting casings of gas turbine engines and mounting method | |
| US20140026591A1 (en) | Axial retention for fasteners in fan joint | |
| US20230407813A1 (en) | Assembly for a turbomachine | |
| US6994519B2 (en) | Apparatus and methods for coupling axially aligned turbine rotors | |
| JPH051567A (en) | Gas turbine | |
| US11821330B1 (en) | Aperture pattern for gas turbine engine component with integral alignment feature | |
| US11187099B1 (en) | Turbine shroud with containment features | |
| US11208911B2 (en) | Turbine shroud ring segments with ceramic matrix composite components | |
| US11873725B2 (en) | Fastener cover for flanged joint | |
| US20230258210A1 (en) | Flange assembly for fastener retention and method for assembling same | |
| US11746658B2 (en) | Turbine shroud with containment features | |
| US9279325B2 (en) | Turbomachine wheel assembly having slotted flanges | |
| JPH08165903A (en) | Fixed structure of turbine stator blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |