Mounting flange structure for gas turbine engine case connection and mounting method

Abstract

The application discloses a mounting flange structure and mounting method for gas turbine engine casing connection, the mounting flange structure is fixedly arranged with multiple buckles on the mounting edges of two casings in a circumferential direction, when assembling, only one circle of buckles on one mounting edge of the casings is staggered with one circle of buckles on the other mounting edge of the casings in a circumferential direction, and a circumferential mounting groove is formed between the two circles of buckles, a clamp is mounted in the mounting groove and locked by a locking piece, the mounting edges of the two casings are tightly attached, and the axial connection of the two casings is realized. The mounting and dismounting is very convenient, the quick connection and disassembly of the casing can be realized, the clamp is clamped in the circumferential mounting groove formed by the two circles of buckles, the reliable axial connection of the two casings can be realized, the mounting edges of the two casings are tightly attached, and the air leakage phenomenon at the connection of the two mounting edges can be effectively reduced.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of gas turbine engine, in particular, to a mounting flange structure for gas turbine engine casing connection. BACKGROUND

[0002] The gas turbine engine is a device for converting chemical energy of fuel into mechanical work. In the field of gas turbine engine, the inner and outer casings of the engine are generally divided into multiple sections, such as compressor casing, combustion chamber casing, turbine casing, reducer casing, etc. The casing plays a role of containing flow channel, transmitting axial force and torque, etc. The existing casings are connected to each other by screws and nuts in the axial direction. Specifically, the casing is provided with a mounting edge at the connection end, a large number of through holes are formed on the mounting edge in the circumferential direction, the through holes on the mounting edges of the adjacent two casings correspond to each other in pairs, and the screws pass through the through holes and cooperate with the nuts to fix the two mounting edges together.

[0003] However, the existing screw and nut fastening structure is very time-consuming to disassemble. In order to achieve reliable fastening connection, dozens of screws and nuts are generally arranged on the mounting edge in the circumferential direction. The more the number of screws and nuts, the more reliable the fastening, but the disassembly takes more time. In addition, if the working temperature at the mounting edge is high, for example, the temperature at the mounting edge of the combustion chamber casing is high, the screws and nuts are easy to stick together, and the difficulty and time consumption of disassembly are greater. When performing engine component or whole machine test, it is often necessary to complete the task of multiple schemes and multiple engines, which is time-consuming and affects the test task node. Moreover, when the engine has an unforeseen failure and needs to be disassembled for inspection, it cannot be quickly disassembled. In addition, the fastening force is not uniformly distributed in the area between adjacent screws, which is easy to cause gas leakage. SUMMARY

[0004] The present application provides a mounting flange structure for gas turbine engine casing connection to solve the technical problem of inconvenient disassembly of the existing gas turbine engine casing connected by screws and nuts.

[0005] According to one aspect of the present application, a mounting flange structure for gas turbine engine casing connection is provided, which comprises a buckle, a clamp and a locking piece. The buckle is fixed and installed on the mounting edge of the first casing and the mounting edge of the second casing in the circumferential direction. When the first casing and the second casing are assembled, one circle of buckles on the mounting edge of the first casing and one circle of buckles on the mounting edge of the second casing are sequentially staggered in the circumferential direction, and a circumferential installation groove is formed between the two circles of buckles. The clamp is installed in the installation groove and locked by the locking piece, so that the mounting edge of the first casing and the mounting edge of the second casing are tightly fitted.

[0006] Further, the buckle is a rotating body sector segment with Z-shaped cross section, and the rotation axis thereof coincides with the theoretical axis of the casing.

[0007] Further, the clasp comprises a first working surface, a second working surface and a third working surface, the first working surface is in contact with the outer side plane of the mounting edge, the second working surface is in contact with the outer side cylinder surface of the mounting edge, and the third working surface is in contact with the positioning working surface on both sides of the clasp.

[0008] Further, the first working surface is a plane, the second working surface is a cylinder surface, and the third working surface is a tapered surface with the same taper as the tapered surface on both sides of the clasp.

[0009] Further, the circumferential gap between the adjacent clasp on the two mounting edges is the same, and the angle between the adjacent clasp on the two mounting edges is the same as the sector angle of the clasp, so that when the two casings are assembled, the clasp on one side of the mounting edge is just clamped between the adjacent two clasp on the other side of the mounting edge, thereby realizing the circumferential positioning of the two mounting edges.

[0010] Further, the two mounting edges are further circumferentially positioned by positioning pins or positioning grooves.

[0011] Further, the number of the clasp is at least two, the clasp is provided with a tongue, the tongue is provided with a through hole, the adjacent two clasp are locked by a locking piece, and the at least two clasp cover the circumferential 360° area after being locked.

[0012] Further, the number of the clasp is two, and each clasp covers a circumferential 180° area.

[0013] In addition, the application also provides a mounting method for the casing connection of a gas turbine engine, which adopts the mounting flange structure as described above, and comprises the following contents:

[0014] A plurality of clasp are fixed on the mounting edge of the first casing and the mounting edge of the second casing in a circumferential uniform interval;

[0015] The first casing and the second casing are matched, so that the clasp on the mounting edge of the first casing and the clasp on the mounting edge of the second casing are circumferentially staggered in sequence, and a circumferential mounting channel is formed between the two clasp;

[0016] The clasp is installed in the circumferential mounting channel and locked by a locking piece, so that the mounting edge of the first casing and the mounting edge of the second casing are closely contacted.

[0017] Further, when the first casing and the second casing are matched, the clasp on one side of the mounting edge is just clamped between the adjacent two clasp on the other side of the mounting edge, so as to realize the circumferential positioning of the two mounting edges, and a circumferential mounting channel is formed between the third working surfaces of the two clasp.

[0018] The present application has the following effects:

[0019] The mounting flange structure for gas turbine engine casing connection of the present application, by fixing a plurality of buckles on the mounting edges of the two casings in uniform circumferential intervals respectively, only needs to stagger the buckles on one mounting edge of one casing with the buckles on one mounting edge of the other casing in circumferential direction, and form a circumferential mounting groove between the two buckles, and then install the clamp in the mounting groove and lock it by the locking member, so as to tightly fit the mounting edges of the two casings, thereby realizing the axial connection of the two casings. When the two casings need to be disassembled, only need to loosen the locking member on the clamp, and take out the clamp from the mounting groove, so as to separate the two casings. The mounting flange structure for gas turbine engine casing connection of the present application is very convenient to assemble and disassemble, can realize the quick connection and disassembly of the casing, and the clamp is clamped in the circumferential mounting groove formed by the two buckles, which can realize the reliable axial connection of the two casings, and tightly fit the mounting edges of the two casings, so as to effectively reduce the air leakage phenomenon at the connection of the two mounting edges, and is especially suitable for the test piece casing of the aviation turboshaft engine, which can greatly shorten the disassembly time, reduce the disassembly difficulty, shorten the test preparation time, and reduce the air leakage of the mounting edges.

[0020] In addition, the mounting method for gas turbine engine casing connection of the present application also has the above advantages.

[0021] In addition to the above described objects, features and advantages, the present application has other objects, features and advantages. The present application will be further described below with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0022] The accompanying drawings, which form a part of this application, are included to provide a further understanding of the application, and are incorporated in and constitute a part of this application. The embodiments of the present application illustrated in the drawings are intended to explain the present application and are not intended to limit the present application. In the drawings:

[0023] Figure 1 is a schematic view of the buckle of the preferred embodiment of the present application.

[0024] Figure 2 is a schematic view of the front view structure of the buckle of the preferred embodiment of the present application.

[0025] Figure 3 is a schematic view of the left view structure of the buckle of the preferred embodiment of the present application.

[0026] Figure 4 is a schematic view of the structure of the clamp of the preferred embodiment of the present application.

[0027] Figure 5 is a schematic view of the partial structure of the through hole on the tongue of the clamp of the preferred embodiment of the present application.

[0028] Figure 6 is a schematic view of the partial structure of the buckle fixed on the mounting edge of the first casing in the preferred embodiment of the present application.

[0029] Figure 7 is a schematic view of the structure of the clasp of the clamp and the buckle on the mounting edge of the first casing in the preferred embodiment of the present application.

[0030] Figure 8 is a schematic view of the structure of the clasp of the clamp and the buckle on the mounting edge of the second casing in the preferred embodiment of the present application.

[0031] Figure 9 is a schematic view of the structure of the circumferential mounting channel formed between the third working surfaces of the two buckles in the preferred embodiment of the present application.

[0032] Figure 10 is a schematic view of the structure of the clamp locked in the circumferential mounting channel by the locking member in the preferred embodiment of the present application.

[0033] Figure 11 is a schematic view of the partial structure of the mounting flange structure for the casing connection of the gas turbine engine in the preferred embodiment of the present application.

[0034] BRIEF DESCRIPTION OF DRAWINGS

[0035] 1. buckle; 2. clamp; 3. mounting edge of the first casing; 4. mounting edge of the second casing; 5. locking member; 101. first working surface; 102. second working surface; 103. third working surface; 301. outer flat surface; 302. outer cylindrical surface; 201. tongue; 202. through hole; 203. positioning working surface. DETAILED DESCRIPTION

[0036] The embodiments of the present application are described in detail below with reference to the accompanying drawings, but the present application can be implemented in various different ways as defined and covered by the following description.

[0037] As Figures 1 to 11As shown, the preferred embodiment of the present application provides a mounting flange structure for gas turbine engine casing connection, which comprises buckles 1, clamps 2 and locking members 5. The buckles 1 are fixed and installed on the mounting edges 3 and 4 of the first and second casings in a circumferential uniform interval. When the first and second casings are assembled, the buckles 1 on the mounting edge 3 of the first casing and the buckles 1 on the mounting edge 4 of the second casing are circumferentially staggered in sequence, and a circumferential mounting groove is formed between the two rows of buckles 1. The clamp 2 is installed in the mounting groove and locked by the locking member 5, so that the mounting edges 3 and 4 of the first and second casings are tightly fitted. When the first and second casings need to be disassembled, the locking member 5 is loosened, and then the clamp 2 is removed, so that the first and second casings can be separated from each other. The locking member 5 is locked by screw and nut or bolt and nut.

[0038] It can be understood that the mounting flange structure for gas turbine engine casing connection of the embodiment can realize the axial connection of the two casings by fixing and installing a plurality of buckles 1 on the mounting edges of the two casings in a circumferential uniform interval. When assembling, only the buckles 1 on one mounting edge of one casing and the buckles 1 on the mounting edge of the other casing need to be circumferentially staggered in sequence, and a circumferential mounting groove is formed between the two rows of buckles 1. The clamp 2 is installed in the mounting groove and locked by the locking member 5, so that the mounting edges of the two casings are tightly fitted, thereby realizing the axial connection of the two casings. When disassembling the two casings, only the locking member 5 on the clamp 2 needs to be loosened, and then the clamp 2 is removed from the mounting groove, so that the two casings can be separated. The mounting flange structure for gas turbine engine casing connection of the present application is very convenient to assemble and disassemble, can realize the rapid connection and disassembly of the casing, and the clamp 2 is clamped in the circumferential mounting groove formed by the two rows of buckles 1, which can realize the reliable axial connection of the two casings and tightly fit the mounting edges of the two casings, thereby effectively reducing the air leakage phenomenon at the connection between the two mounting edges, and is particularly suitable for test piece casings of aviation turboshaft engines, which can greatly shorten the disassembly and assembly time, reduce the disassembly and assembly difficulty, shorten the test preparation time, and reduce the air leakage of the mounting edges.

[0039] Optionally, the buckle 1 is a Z-shaped cross-section rotating body sector, and the rotation axis of the buckle 1 coincides with the theoretical axis of the casing. The buckle 1 can be fixedly installed on the installation edge by welding, bolt connection or rivet connection and the like. Specifically, the buckle 1 comprises a first working surface 101, a second working surface 102 and a third working surface 103. The first working surface 101 is attached to the outer side plane 301 of the installation edge, the second working surface 102 is attached to the outer side cylindrical surface 302 of the installation edge, and the third working surface 103 is attached to the positioning working surface 203 on both sides of the clamp 2. 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 with the same taper as the taper of the positioning working surface 203 on both sides of the clamp 2. The second working surface 102 of the buckle 1 covers the installation edge and is attached to the outer side cylindrical surface 302, which can effectively reduce the radial air leakage of the installation edge.

[0040] It can be understood that the clamp 2 is a rotating body sector with a mouth-shaped cross-section. Optionally, the number of the clamps 2 is at least two. The clamp 2 is provided with a tongue 201, and a through hole 202 is formed in the tongue 201. Adjacent two clamps 2 are locked by a locking piece 5. After the at least two clamps 2 are locked, they cover a circumferential 360° area to ensure uniform distribution of locking force. The number of the clamps 2 is n, and each clamp 2 covers a circumferential 360° / n area. Preferably, the number of the clamps 2 is two, and each clamp 2 covers a circumferential 180° area.

[0041] It can be understood that the circumferential gap between adjacent buckles 1 on the two installation edges is the same, and the angle between adjacent buckles 1 in the circumferential direction is the same as the sector angle α of the buckle 1. When the two casings are assembled, the buckle 1 on one installation edge is just clamped between the adjacent two buckles 1 on the other installation edge, so that the circumferential positioning of the two installation edges can be realized by the mutual misalignment of the two rows of buckles 1. Optionally, the two installation edges can also be circumferentially positioned by positioning pins or positioning grooves to improve the reliability of the circumferential positioning. When the two casings are assembled, the third working surfaces 103 of the buckles 1 on different installation edges form an installation groove along the circumferential direction. The clamp 2 is installed in the installation groove, and the positioning working surfaces 203 on both sides of the clamp 2 are attached to the third working surfaces 103 of the buckles 1 on the two installation edges, respectively. Then the locking piece 5 is locked. Under the locking action of the locking piece 5, the clamp 2 tends to shrink inward along the radial direction, thereby extruding the two installation edges to move away from each other, so that the two installation edges move towards each other and tightly fit together. For example, Figure 10As shown, one circle of buckles 1 on the mounting edge 3 of the first casing is moved to the left under the extrusion of the clamp 2, and one circle of buckles 1 on the mounting edge 4 of the second casing is moved to the right under the extrusion of the clamp 2, so that the mounting edge 3 of the first casing is moved to the right, and the mounting edge 4 of the second casing is moved to the left, and finally the two mounting edges are tightly attached together.

[0042] In addition, another embodiment of the present application also provides a mounting method for gas turbine engine casing connection, preferably using the mounting flange structure as described above, comprising the following contents:

[0043] A plurality of buckles 1 are fixed and arranged on the mounting edge 3 of the first casing and the mounting edge 4 of the second casing respectively and uniformly spaced in the circumferential direction;

[0044] The first casing is matched with the second casing, so that one circle of buckles 1 on the mounting edge 3 of the first casing and one circle of buckles 1 on the mounting edge 4 of the second casing are sequentially staggered with each other in the circumferential direction, and a circumferential mounting groove is formed between the two circles of buckles 1;

[0045] The clamp 2 is installed in the circumferential mounting groove 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.

[0046] It can be understood that the mounting method for gas turbine engine casing connection of the present embodiment, by fixing and arranging a plurality of buckles 1 on the mounting edges of the two casings respectively and uniformly spaced in the circumferential direction, when assembling the two casings, only one circle of buckles 1 on the mounting edge of one casing and one circle of buckles 1 on the mounting edge of the other casing are sequentially staggered with each other in the circumferential direction, and a circumferential mounting groove is formed between the two circles of buckles 1, and the clamp 2 is installed in the mounting groove and locked by the locking member 5, so that the mounting edges of the two casings are tightly attached, thereby realizing the axial connection of the two casings. When disassembling the two casings, only the locking member 5 on the clamp 2 is loosened, and the clamp 2 is taken out of the mounting groove, so that the two casings can be separated. The mounting method for gas turbine engine casing connection of the present application can realize the quick connection and disassembly of the casing, and the clamp 2 is clamped in the circumferential mounting groove formed between the two circles of buckles 1, which can realize the reliable axial connection of the two casings, and the mounting edges of the two casings are tightly attached, which can effectively reduce the air leakage phenomenon at the connection of the two mounting edges, and is particularly suitable for test piece casings of aviation turboshaft engines, which can greatly shorten the disassembly time, reduce the disassembly difficulty, shorten the test preparation time, and reduce the air leakage of the mounting edges.

[0047] It can be understood that when the first casing is matched with the second casing, the buckles 1 on one side mounting edge are clamped between the adjacent two buckles 1 on the other side mounting edge, so as to realize the circumferential positioning of the two mounting edges, and a circumferential mounting groove is formed between the third working surfaces 103 of the two circles of buckles 1.

[0048] The above description is only the preferred embodiment of the present application and is not intended to limit the present application. The present application can be variously changed and modified by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the present application.

Claims

1. A mounting flange structure for a gas turbine engine case joint, characterized by, The buckle (1) is a rotating body sector with Z-shaped cross section, and the rotating axis coincides with the theoretical axis of the casing; the buckle (1) comprises a first working surface (101), a second working surface (102) and a third working surface (103), the first working surface (101) is attached to the outside plane (301) of the mounting edge, the second working surface (102) is attached to the outside cylindrical surface (302) of the mounting edge, the third working surface (103) is attached to the positioning working surface (203) on both sides of the buckle (2), 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 tapered surface with the same taper as the taper of the positioning working surface (203) on both sides of the buckle (2), the second working surface (102) of the buckle (1) covers the mounting edge and is attached to the outside cylindrical surface (302), which can effectively reduce the radial air leakage of the mounting edge; the circumferential gap between the adjacent buckles (1) on the two mounting edges is the same, and the angle between the adjacent buckles (1) in the circumferential direction is the same as the sector angle of the buckle (1), when the two casings are assembled, the buckle (1) on one side of the mounting edge is just clamped between the adjacent two buckles (1) on the other side of the mounting edge, thereby realizing the circumferential positioning of the two mounting edges. The two mounting edges are also circumferentially positioned by positioning pins or positioning grooves.

2. The mounting flange structure for a gas turbine engine case joint of claim 1, wherein, The number of the buckles (2) is at least two, the buckle (2) is provided with a tongue (201), a through hole (202) is formed in the tongue (201), the adjacent two buckles (2) are locked by the locking member (5), and the at least two buckles (2) cover a circumferential 360° area after being locked.

3. The mounting flange structure for a gas turbine engine case joint of claim 1, wherein, The number of the buckles (2) is 2, and each buckle (2) covers a circumferential 180° area.

4. The mounting flange structure for a gas turbine engine case joint of claim 3, wherein, The buckle (1) is a rotating body sector with Z-shaped cross section, and the rotating axis coincides with the theoretical axis of the casing; the buckle (1) comprises a first working surface (101), a second working surface (102) and a third working surface (103), the first working surface (101) is attached to the outside plane (301) of the mounting edge, the second working surface (102) is attached to the outside cylindrical surface (302) of the mounting edge, the third working surface (103) is attached to the positioning working surface (203) on both sides of the buckle (2), 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 tapered surface with the same taper as the taper of the positioning working surface (203) on both sides of the buckle (2), the second working surface (102) of the buckle (1) covers the mounting edge and is attached to the outside cylindrical surface (302), which can effectively reduce the radial air leakage of the mounting edge; the circumferential gap between the adjacent buckles (1) on the two mounting edges is the same, and the angle between the adjacent buckles (1) in the circumferential direction is the same as the sector angle of the buckle (1), when the two casings are assembled, the buckle (1) on one side of the mounting edge is just clamped between the adjacent two buckles (1) on the other side of the mounting edge, thereby realizing the circumferential positioning of the two mounting edges.

5. A method of mounting a gas turbine engine case connection using the mounting flange structure of any one of claims 1 to 4, characterized in that, The two mounting edges are also circumferentially positioned by positioning pins or positioning grooves. The number of the buckles (2) is at least two, the buckle (2) is provided with a tongue (201), a through hole (202) is formed in the tongue (201), the adjacent two buckles (2) are locked by the locking member (5), and the at least two buckles (2) cover a circumferential 360° area after being locked. The number of the buckles (2) is 2, and each buckle (2) covers a circumferential 180° area. The buckle (1) is a rotating body sector with Z-shaped cross section, and the rotating axis coincides with the theoretical axis of the casing; the buckle (1) comprises a first working surface (101), a second working surface (102) and a third working surface (103), the first working surface (101) is attached to the outside plane (301) of the mounting edge, the second working surface (102) is attached to the outside cylindrical surface (302) of the mounting edge, the third working surface (103) is attached to the positioning working surface (203) on both sides of the buckle (2), 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 tapered surface with the same taper as the taper of the positioning working surface (203) on both sides of the buckle (2), the second working surface (102) of the buckle (1) covers the mounting edge and is attached to the outside cylindrical surface (302), which can effectively reduce the radial air leakage of the mounting edge; the circumferential gap between the adjacent buckles (1) on the two mounting edges is the same, and the angle between the adjacent buckles (1) in the circumferential direction is the same as the sector angle of the buckle (1), when the two casings are assembled, the buckle (1) on one side of the mounting edge is just clamped between the adjacent two buckles (1) on the other side of the mounting edge, thereby realizing the circumferential positioning of the two mounting edges. When the first casing is matched with the second casing, the buckle (1) on one side mounting edge is just buckled between the adjacent two buckles (1) on the other side mounting edge, so as to realize the circumferential positioning of the two mounting edges, and form a circumferential mounting channel between the third working surfaces (103) of the two buckles (1).

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