CN217635754U

CN217635754U - Be used for outer flame tube reinforcing apparatus of aeroengine

Info

Publication number: CN217635754U
Application number: CN202221149184.4U
Authority: CN
Inventors: 李玮林
Original assignee: Laizhou Zhongwei Machinery Co ltd
Current assignee: Laizhou Zhongwei Machinery Co ltd
Priority date: 2022-05-13
Filing date: 2022-05-13
Publication date: 2022-10-21
Anticipated expiration: 2032-05-13

Abstract

The utility model discloses a be used for outer flame tube reinforcing apparatus of aeroengine, belong to aerospace technical field, this be used for outer flame tube reinforcing apparatus of aeroengine, which comprises a housing, annular flame tube and compressor, the inside round that is provided with of casing keeps off the platform, keep off the bench and seted up a plurality of outer constant head tanks, be provided with a plurality of outer limits of extending on the annular flame tube, the outer screw hole has been seted up with the correspondence on the outer limit to arbitrary outer constant head tank, threaded connection has the mounting in the external screw thread, all adopt the welding mode in the flame tube structural design of conventional aeroengine direct current combustion chamber, but this mode manufacturing cost is higher, all seted up the constant head tank along the edge through keeping off the platform and connecting, all correspond on the outer wall of annular flame tube and inner wall and install the extension limit and with the constant head tank one-to-one, make the casing, be located the same axis all the time between annular flame tube and the compressor, and fixed through the mounting, annular flame tube's detachability and stability have been improved.

Description

Be used for outer flame tube reinforcing apparatus of aeroengine

Technical Field

The utility model belongs to the technical field of aerospace, in particular to be used for outer flame tube reinforcing apparatus of aeroengine.

Background

At present, a welding mode is adopted in the structural design of a flame tube of a direct-current combustion chamber of a conventional aircraft engine, a cap, a flame tube head ring, a flame tube outer ring and a flame tube inner ring form an integral structure of the flame tube after being welded, stress concentration is easily generated at the position of a welding line along with the increase of service time, the welding line becomes a main breakthrough of cracks, expansion cracks are generated on the flame tube, and the service life of the flame tube is seriously influenced.

SUMMERY OF THE UTILITY MODEL

To solve the problems mentioned in the background art, the present invention provides an outer flame tube reinforcement device for an aircraft engine to solve the problems mentioned in the background art.

The above technical object of the present invention can be achieved by the following technical solutions:

the utility model provides a be used for outer flame tube reinforcing apparatus of aeroengine, includes casing, annular flame tube and compressor, annular flame tube includes outer wall and inner wall, form the high-temperature gas outlet between outer wall and the inner wall, the casing inside integrated into one piece formula is provided with round fender platform, and a round forms annular combustion chamber space between fender platform and the annular flame tube, and a round fender platform is close to one side of annular flame tube and has seted up a plurality of outer constant head tanks along self axial equidistance, the outer wall tip equidistance that is equipped with on the annular flame tube extends and is provided with a plurality of outer extending sides, a plurality of outer extending sides and a plurality of outer constant head tanks one-to-one, and arbitrary outer constant head tank corresponds with outer extending side and has seted up outer screw hole, threaded connection has the mounting in the outer screw hole;

wherein, the tip that the inner wall is close to compressor one end has a plurality of interior limits of extending along extending outward along self axial, be provided with the round on the surface of compressor and connect the edge, the round connect the edge equidistance and seted up a plurality of interior constant head tanks, it is a plurality of interior limit and a plurality of interior constant head tank one-to-one, arbitrary interior constant head tank and interior on-extending correspond and seted up the internal thread hole, internal thread hole female connection has same mounting.

All adopt the welding mode in conventional aeroengine direct current combustion chamber's flame tube structural design, but this mode need be with the casing, annular flame tube and compressor are fixed on same axis, and the production cost is improved, all seted up the constant head tank along the edge through keeping off the platform and connecting, all correspond to install on annular flame tube's outer wall and inner wall extend the limit and with the constant head tank one-to-one, make the casing, lie in same axis all the time between annular flame tube and the compressor, and it is fixed through the mounting, the detachability and the stability of annular flame tube have been improved.

As a preferred, the mounting is including installing the location bush in outer screw hole and interior screw hole respectively, install fastening bolt in the location bush, fastening bolt runs through one end threaded connection of location bush has fastening nut.

As a preferred aspect of the present invention, a single disc washer is disposed between the fastening nut and the positioning bushing, the opposite surfaces of the single disc washer and the fastening nut are respectively provided with a large tooth surface and a large caulking groove, the large caulking groove corresponds to the large tooth surface, the opposite surfaces of the single disc washer and the positioning bushing are respectively provided with a small tooth surface and a small caulking groove, and the small caulking groove corresponds to the small tooth surface;

wherein, the single large tooth surface is an inclined surface with an oblique angle alpha and radiates to the circumference by taking the central line of the fastening bolt as the center;

wherein the fastening bolt has a lifting angle 'beta'.

As an optimization of the utility model, the round connect on the surface of border and compressor the equidistance install a plurality of triangle even muscle.

As a preferred, the annular flame tube adopts the multistage formula structure, adopts radial mode of overlapping mutually between every section, and all has seted up a plurality of cooling holes along self axial in every section.

As an optimization of the utility model, a plurality of mounting holes have been seted up to junction between outer wall and the inner wall, be provided with the inlet pipe in the mounting hole, swirler and nozzle are installed to the one end that the inlet pipe is located annular flame tube.

As a preferred aspect of the present invention, the nozzle is located at the axis of the swirler.

To sum up, the utility model discloses mainly have following beneficial effect:

first, all adopt the welding mode in the flame tube structural design of conventional aeroengine direct current combustion chamber, but this mode need be with the casing, annular flame tube and compressor are fixed on same axis, production cost is improved, through keeping off the platform and connect and all seted up the constant head tank along the edge, all correspond on annular flame tube's outer wall and inner wall and install the extension limit and with the constant head tank one-to-one, make the casing, lie in same axis all the time between annular flame tube and the compressor, and it is fixed through the mounting, the detachability and the stability of annular flame tube have been improved.

Second, form wedge effect between single dish packing ring and the positioning bush and the fastening nut of both sides, can effectually prevent that the rotatory pine that fastening bolt rotation, subside and lax arouse from taking off, great improvement locking bolt's fixed effect.

Drawings

Fig. 1 is a schematic structural diagram of the present invention;

fig. 2 is an enlarged schematic view of the structure at a in fig. 1 of the present invention;

FIG. 3 is a schematic structural view of a portion of the annular flame tube of the present invention;

fig. 4 is a schematic view of the fixing member structure of the present invention.

Reference numerals are as follows: 1. a housing; 2. an annular flame tube; 201. an outer wall; 202. an inner wall; 203. a high-temperature gas outlet; 204. a cooling hole; 205. mounting holes; 3. a compressor; 4. blocking the platform; 401. positioning a groove; 5. an annular combustion chamber space; 6. an outer extended edge; 7. an external threaded hole; 8. an inner extending edge; 9. connecting the edge; 901. an inner positioning groove; 10. an internally threaded bore; 11. positioning the bushing; 1101. a small caulking groove; 12. fastening a bolt; 13. fastening a nut; 1301. a large caulking groove; 14. a single disc washer; 1401. a large tooth surface; 1402. A small tooth surface; 15. connecting the ribs in a triangular manner; 16. a feed pipe; 17. a swirler; 18. and (4) a nozzle.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Examples

Referring to fig. 1-4, an outer flame tube reinforcing device for an aircraft engine comprises a casing 1, an annular flame tube 2 and a compressor 3, wherein the annular flame tube 2 comprises an outer wall 201 and an inner wall 202, a high-temperature gas outlet 203 is formed between the outer wall 201 and the inner wall 202, a circle of baffle table 4 is integrally arranged in the casing 1, an annular combustion chamber space 5 is formed between the circle of baffle table 4 and the annular flame tube 2, a plurality of outer positioning slots 401 are axially and equidistantly arranged on one side of the circle of baffle table 4 close to the annular flame tube 2 along the axial direction of the baffle table, a plurality of outer extending edges 6 are equidistantly arranged on the end portion of the outer wall 201 arranged on the annular flame tube 2 in an extending manner, the plurality of outer extending edges 6 are in one-to-one correspondence with the plurality of outer positioning slots 401, outer threaded holes 7 are correspondingly arranged on any one of the outer positioning slots 401 and the outer extending edges 6, and a fixing piece is connected with the inner threads of the outer threaded holes 7;

wherein, the tip that inner wall 202 is close to compressor 3 one end has a plurality of interior flanges 8 along self axial outer edge extension, is provided with the round on compressor 3's the surface and connects the flange 9, and the equidistant a plurality of interior constant head tanks 901 of having seted up on the flange 9 are connected to the round, and a plurality of interior flanges 8 and a plurality of interior constant head tanks 901 one-to-one have been extended to a plurality of, and internal thread hole 10 has same mounting in arbitrary interior constant head tank 901 and the interior corresponding of extending on the flange 8, and internal thread hole 10 female connection has.

The fixing piece comprises a positioning bush 11 respectively installed in the external threaded hole 7 and the internal threaded hole 10, a fastening bolt 12 is installed in the positioning bush 11, and one end of the fastening bolt 12 penetrating through the positioning bush 11 is in threaded connection with a fastening nut 13.

In the application, all adopt the welding mode in the flame tube structural design of conventional aeroengine direct current combustion chamber, but this mode needs casing 1, annular flame tube 2 and compressor 3 fix on same axis, production cost is improved, through all having seted up the constant head tank on keeping off platform 4 and connecting edgewise 9, all correspond to install the extension limit and with the constant head tank one-to-one on the outer wall 201 of annular flame tube 2 and inner wall 202, make casing 1, lie in same axis all the time between annular flame tube 2 and the compressor 3, and it is fixed through the mounting, the detachability and the stability of annular flame tube 2 have been improved.

Specifically, referring to fig. 4, in order to improve the anti-loosening performance of the fastening bolt 12, a single disc washer 14 is arranged between the fastening nut 13 and the positioning bushing 11, a large tooth surface 1401 and a large caulking groove 1301 are respectively arranged on the opposite surfaces of the single disc washer 14 and the fastening nut 13, the large caulking groove 1301 corresponds to the large tooth surface 1401, a small tooth surface 1402 and a small caulking groove 1101 are respectively arranged on the opposite surfaces of the single disc washer 14 and the positioning bushing 11, and the small caulking groove 1101 corresponds to the small tooth surface 1402;

wherein, the single large tooth surface 1401 is an inclined surface with an oblique angle of 'alpha' and radiates to the circumference with the center line of the fastening bolt 12 as the center;

wherein the lifting angle "β" of the fastening bolt 12.

In application, the set oblique angle is 'alpha' larger than the lift angle 'beta', a wedge effect is formed between the single disc washer 14 and the positioning bushes 11 and the fastening nuts 13 on the two sides, so that the rotation loosening caused by the rotation, settlement and loosening of the fastening bolt 12 can be effectively prevented, and the fixing effect of the fastening bolt 12 is greatly improved.

Specifically, referring to fig. 1, in order to improve the bearing capacity of the connecting edge 9, a plurality of triangular connecting ribs 15 are equidistantly installed on the outer surface of the ring of connecting edge 9 and the compressor 3.

Specifically, referring to fig. 3, in order to cool the inside of the annular flame tube 2, the annular flame tube 2 is of a multi-section structure, each section is sleeved with another section in a radial direction, and each section is provided with a plurality of cooling holes 204 along its own axial direction.

Specifically, referring to the drawings, in order to form a plurality of mounting holes 205 at the connecting position between the outer wall 201 and the inner wall 202, a feed pipe 16 is arranged in the mounting holes 205, and a swirler 17 and a nozzle 18 are installed at one end of the feed pipe 16 located in the annular flame tube 2.

Wherein the nozzle 18 is located at the axial center of the swirler 17.

In use, fuel from the nozzle 18 is mixed with incoming air and combusted to form thrust.

The use principle and the advantages are as follows: the outer extending edge 6 corresponds to the outer positioning grooves 401, the inner extending edge 8 corresponds to the inner positioning grooves 901, the casing 1, the annular flame tube 2 and the compressor 3 are fixed on the same axis and fixed through the fastening bolt 12, a wedge effect is formed between the single disc washer 14 and the positioning bushes 11 and the fastening nuts 13 on two sides, the fastening bolt 12 can be effectively prevented from rotating, settling and loosening, and the fixing effect of the fastening bolt 12 is greatly improved.

Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims

1. The utility model provides a be used for outer flame tube reinforcing apparatus of aeroengine, includes casing (1), annular flame tube (2) and compressor (3), its characterized in that: the annular flame tube (2) comprises an outer wall (201) and an inner wall (202), a high-temperature gas outlet (203) is formed between the outer wall (201) and the inner wall (202), a circle of baffle table (4) is integrally arranged in the casing (1), a circle of annular combustion chamber space (5) is formed between the baffle table (4) and the annular flame tube (2), a plurality of outer positioning grooves (401) are formed in one side, close to the annular flame tube (2), of the baffle table (4) in one circle along the axial direction of the baffle table at equal intervals, a plurality of outer extending edges (6) are arranged at the end part of the outer wall (201) arranged on the annular flame tube (2) in an extending mode at equal intervals, the plurality of outer extending edges (6) correspond to the plurality of outer positioning grooves (401) one to one, outer threaded holes (7) are correspondingly formed in any one of the outer positioning grooves (401) and the outer extending edges (6), and the outer threaded holes (7) are connected with inner threads;

the inner wall (202) is close to the end portion of one end of the gas compressor (3) and is provided with a plurality of inner extending edges (8) in an extending mode along the axial direction of the end portion, the outer surface of the gas compressor (3) is provided with a circle of connecting edges (9), a plurality of inner positioning grooves (901) are formed in the circle of connecting edges (9) at equal intervals, the inner extending edges (8) correspond to the inner positioning grooves (901) in a one-to-one mode, an inner threaded hole (10) is formed in the inner positioning grooves (901) and the inner extending edges (8) in a corresponding mode, and the inner threaded hole (10) is connected with the same fixing piece in an inner threaded mode.

2. The outer flame tube reinforcement device for the aircraft engine as claimed in claim 1, wherein: the fixing piece comprises a positioning bushing (11) which is respectively installed in an external threaded hole (7) and an internal threaded hole (10), a fastening bolt (12) is installed in the positioning bushing (11), and one end of the fastening bolt (12) penetrating through the positioning bushing (11) is connected with a fastening nut (13) through threads.

3. The outer flame tube reinforcement device for the aircraft engine as claimed in claim 2, wherein: a single disc washer (14) is arranged between the fastening nut (13) and the positioning bushing (11), a large tooth surface (1401) and a large caulking groove (1301) are respectively arranged on the opposite surfaces of the single disc washer (14) and the fastening nut (13), the large caulking groove (1301) corresponds to the large tooth surface (1401), a small tooth surface (1402) and a small caulking groove (1101) are respectively arranged on the opposite surfaces of the single disc washer (14) and the positioning bushing (11), and the small caulking groove (1101) corresponds to the small tooth surface (1402);

wherein, the single large tooth surface (1401) is an inclined surface with an inclined angle alpha and is radiated to the circumference by taking the central line of the fastening bolt (12) as the center;

wherein the fastening bolt (12) has a lifting angle 'beta'.

4. The outer flame tube reinforcement device for the aircraft engine as claimed in claim 1, wherein: and a plurality of triangular connecting ribs (15) are arranged on the outer surface of the connecting edge (9) and the air compressor (3) at equal intervals.

5. The outer flame tube reinforcement device for the aircraft engine as claimed in claim 4, wherein: the annular flame tube (2) adopts a multi-section structure, a radial sleeving mode is adopted between each section, and a plurality of cooling holes (204) are formed in each section along the axial direction of the section.

6. The outer flame tube reinforcement device for the aircraft engine as claimed in claim 1, wherein: a plurality of mounting holes (205) have been seted up to junction between outer wall (201) and inner wall (202), be provided with inlet pipe (16) in mounting hole (205), swirler (17) and nozzle (18) are installed to the one end that inlet pipe (16) are located annular flame tube (2).

7. The outer flame tube reinforcement device for the aircraft engine as defined in claim 6, wherein: the nozzle (18) is positioned at the axis of the swirler (17).