CN213749082U

CN213749082U - Combustion chamber test stand of aviation gas turbine

Info

Publication number: CN213749082U
Application number: CN202022660780.6U
Authority: CN
Inventors: 铁克; 韩崇福
Original assignee: Shenyang Hangsuo Power Equipment Co ltd
Current assignee: Shenyang Hangsuo Power Equipment Co ltd
Priority date: 2020-11-17
Filing date: 2020-11-17
Publication date: 2021-07-20
Anticipated expiration: 2030-11-17

Abstract

The utility model discloses an aviation gas turbine's combustion chamber test bench, including concrete base and combustion chamber, the top fixedly connected with installation mechanism of concrete base, the equal fixed mounting in top that installation mechanism's left and right both sides just are located the concrete base has a sliding seat, two the top of sliding seat is respectively through first mount pad and second mount pad fixedly connected with combustor and determine module, installation mechanism includes fixed frame, two brackets of top fixedly connected with of fixed frame, the stand that vertical direction distributes is followed to the outside fixedly connected with of concrete base rear side, the hydraulic stem that vertical direction distributes is followed through support fixedly connected with in the top of stand front side, the utility model relates to an aviation test technical field. This aviation gas turbine's combustion chamber test bench through being provided with two sliding seats for can the activity remove between combustor and the determine module, improved the simple operation nature.

Description

Combustion chamber test stand of aviation gas turbine

Technical Field

The utility model relates to an aviation test technical field specifically is an aviation gas turbine's combustion chamber test bench.

Background

The gas turbine combustor is one of the essential parts in gas turbine engine, and the chemical energy contained in the fuel is converted into heat energy through combustion chemical reaction to form high temperature combustion product to drive turbine to do work, and the heat energy is converted into mechanical energy in different modes according to different purposes.

Through the measurement to combustion chamber export gas temperature help the designer to select suitable turbine blade material and cooling means, current combustion chamber test bench is usually with combustion chamber fixed mounting between combustor and test module, combustor and test module rigidity, very inconvenient when installing.

SUMMERY OF THE UTILITY MODEL

Not enough to prior art, the utility model provides an aviation gas turbine's combustion chamber test bench has solved very inconvenient problem when installing.

In order to achieve the above purpose, the utility model discloses a following technical scheme realizes: the utility model provides an aviation gas turbine's combustion chamber test bench, includes concrete base and combustion chamber, the top fixedly connected with installation mechanism of concrete base, the equal fixed mounting in the top that just is located the concrete base of the left and right both sides of installation mechanism has the sliding seat, two the top of sliding seat is respectively through first mount pad and second mount pad fixedly connected with combustor and detection component, installation mechanism includes fixed frame, the top fixedly connected with two brackets of fixed frame, the outside fixedly connected with of concrete base rear side has the stand along vertical direction distribution, the top of stand front side has the hydraulic stem along vertical direction distribution through support fixedly connected with, the output of hydraulic stem runs through in the support and extends to the below of support and fixedly connected with grip block, the sliding seat includes two spouts, two fixedly connected with baffle between the outside of spout, fixed mounting has the motor on the lateral wall of baffle, the output of motor runs through in the baffle and extends to between two spouts and be connected with the movable block through the lead screw, the top fixedly connected with backup pad of movable block, the left and right both sides of backup pad bottom all rotate and are connected with two gyro wheels, and gyro wheel and spout looks adaptation.

Preferably, the combustor includes the casing, the fixed combustion air port that is provided with in bottom of casing, fixedly connected with locating plate on the right side of combustion air port and the outer wall that is located the casing, shells inner wall's right side fixedly connected with baffle, first mounting groove has been seted up at the middle part of baffle, a plurality of air vents have been seted up to the outside of first mounting groove and on being located the baffle, and a plurality of air vents are the annular array and distribute, the right side fixedly connected with mounting panel of locating plate, it has natural gas pipe to run through in the first mounting groove, natural gas pipe's right-hand member is provided with the flame jet nozzle, the left side fixedly connected with fixed plate of natural gas pipe outer wall.

Preferably, the detection assembly comprises an accelerating spray pipe, a test pipe is fixedly connected to the right side of the accelerating spray pipe, and probes penetrate through the top and the bottom of the outer wall of the test pipe.

Preferably, the second mounting groove has been seted up at the middle part of mounting panel, the right side of casing runs through in the second mounting groove and through locating plate and mounting panel flange joint, natural gas pipe's right-hand member runs through in first mounting groove and through the left side wall flange joint of fixed plate and casing.

Preferably, the combustion chamber joint is between grip block and two brackets, the left and right both sides of combustion chamber all are provided with the flange limit, and two flange limits respectively with the mounting panel with accelerate spray tube flange joint.

Preferably, the ladder groove is all seted up to the bottom of the left and right both sides of concrete foundation, motor fixed mounting is at the top in ladder groove.

Preferably, the output end of the motor is fixedly connected with the screw rod through a coupler, two ends of the screw rod are respectively and rotatably connected with the baffle and the fixed frame through two bearings, and the screw rod penetrates through the movable block and is in threaded connection with the movable block.

Preferably, the support is fixedly connected to the top of the front side of the upright through a tripod, and the support is perpendicular to the upright.

The utility model provides an aviation gas turbine's combustion chamber test bench compares with prior art and possesses following beneficial effect:

(1) this aviation gas turbine's combustion chamber test bench through being provided with two sliding seats for can the activity remove between combustor and the determine module, and when installing, improve the convenience of operation, improve the installation effectiveness.

(2) This aviation gas turbine's combustion chamber test bench sets up the position between combustor and the determine module into adjustable sliding connection mode, can adjust the interval between combustor and the determine module, then to the combustion chamber of different length, can carry out the test operation equally, has improved the flexibility of using, has enlarged application range.

Drawings

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

FIG. 2 is a schematic structural view of the sliding seat of the present invention;

FIG. 3 is a schematic structural view of the mounting mechanism of the present invention;

FIG. 4 is a schematic structural view of the burner of the present invention;

FIG. 5 is a schematic structural view of the detecting assembly of the present invention;

in the figure: 1. a concrete base; 2. a stepped groove; 3. an installation mechanism; 4. a combustion chamber; 5. a sliding seat; 6. a first mounting seat; 7. a second mounting seat; 8. a burner; 9. a detection component; 10. a fixing frame; 11. a bracket; 12. a column; 13. A support; 14. a hydraulic lever; 15. a clamping plate; 16. a chute; 17. a baffle plate; 18. a motor; 19. a screw rod; 20. a movable block; 21. a support plate; 22. a roller; 23. a housing; 24. a combustion air port; 25. positioning a plate; 26. a partition plate; 27. a first mounting groove; 28. a vent hole; 29. mounting a plate; 30. a second mounting groove; 31. a natural gas pipe; 32. a flame spray nozzle; 33. a fixing plate; 34. accelerating the spray pipe; 35. a test tube; 36. and (3) a probe.

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.

Referring to fig. 1-5, the present invention provides a technical solution: a combustion chamber test bed of an aviation gas turbine comprises a concrete base 1 and a combustion chamber 4, wherein the top of the concrete base 1 is fixedly connected with an installation mechanism 3, sliding seats 5 are fixedly installed on the left side and the right side of the installation mechanism 3 and are positioned on the top of the concrete base 1, the tops of the two sliding seats 5 are respectively and fixedly connected with a combustor 8 and a detection assembly 9 through a first installation seat 6 and a second installation seat 7, the installation mechanism 3 comprises a fixed frame 10, the top of the fixed frame 10 is fixedly connected with two brackets 11, the outside of the rear side of the concrete base 1 is fixedly connected with upright posts 12 which are distributed along the vertical direction, the top of the front side of the upright posts 12 is fixedly connected with hydraulic rods 14 which are distributed along the vertical direction through a support 13, the output end of the hydraulic rods 14 penetrates through the support 13 and extends to the lower part of the support 13 and is fixedly connected with a clamping plate 15, the sliding seats 5 comprise two sliding chutes 16, a baffle 17 is fixedly connected between the outer sides of the two chutes 16, a motor 18 is fixedly installed on the outer side wall of the baffle 17, the output end of the motor 18 penetrates through the baffle 17 and extends to a position between the two chutes 16 and is connected with a movable block 20 through a screw rod 19, the top of the movable block 20 is fixedly connected with a support plate 21, two rollers 22 are rotatably connected with the left side and the right side of the bottom of the support plate 21, the rollers 22 are matched with the chutes 16, the burner 8 comprises a shell 23, a combustion-supporting air port 24 is fixedly arranged at the bottom of the shell 23, a positioning plate 25 is fixedly connected on the right side of the combustion-supporting air port 24 and positioned on the outer wall of the shell 23, a partition plate 26 is fixedly connected on the right side of the inner wall of the shell 23, a first installation groove 27 is formed in the middle part of the partition plate 26, a plurality of vent holes 28 are formed outside the first installation groove 27 and positioned on the partition plate 26, and the vent holes 28 are distributed in an annular array, the right side of the positioning plate 25 is fixedly connected with a mounting plate 29, a natural gas pipe 31 penetrates through the first mounting groove 27, the right end of the natural gas pipe 31 is provided with a flame spray nozzle 32, the left side of the outer wall of the natural gas pipe 31 is fixedly connected with a fixing plate 33, the detection assembly 9 comprises an accelerating spray pipe 34, the right side of the accelerating spray pipe 34 is fixedly connected with a test pipe 35, probes 36 penetrate through the top and the bottom of the outer wall of the test pipe 35, the middle part of the mounting plate 29 is provided with a second mounting groove 30, the right side of the shell 23 penetrates through the second mounting groove 30 and is in flange connection with the mounting plate 29 through the positioning plate 25, the right end of the natural gas pipe 31 penetrates through the first mounting groove 27 and is in flange connection with the left side wall of the shell 23 through the fixing plate 33, the combustion chamber 4 is clamped between the clamping plate 15 and the two brackets 11, the left and right sides of the combustion chamber 4 are provided with flange edges, and the two flange edges are respectively in flange connection with the mounting plate 29 and the accelerating spray pipe 34, concrete foundation 1 left side, ladder groove 2 is all seted up to the bottom of right side both sides, 18 fixed mounting of motor is at the top in ladder groove 2, shaft coupling and 19 fixed connection of lead screw are passed through to motor 18's output, 19 both ends of lead screw are rotated through two bearings and baffle 17 and fixed frame 10 respectively and are connected, lead screw 19 run through in the movable block 20 and with 20 threaded connection of movable block, support 13 passes through the top of tripod fixed connection in stand 12 front side, support 13 perpendicular to stand 12, through being provided with two sliding seats 5, make can the mobilization between combustor 8 and the determine module 9, and when installing, operating personnel convenience has been improved, operating personnel's installation effectiveness has been improved.

During operation, firstly, an operator places the combustion chamber 4 on the two brackets 11, and controls the hydraulic rod 14 to enable the clamping plate 15 to clamp and fix the combustion chamber 4, then the operator sequentially controls the two sliding seats 5 to enable the output ends of the motors 18 to rotate, under the action of the screw rod 19, the movable block 20 moves inwards, the movable block 20 drives the supporting plate 21 to move inwards along the two sliding grooves 16 under the action of the four rollers 22, the combustor 8 and the detection assembly 9 both move inwards under the action of the first mounting seat 6 and the second mounting seat 7 until the combustor 8 and the detection assembly 9 are in butt joint with two sides of the combustion chamber 4, the operator respectively closes the two motors 18, the mounting plate 29 on the combustor 8 is in butt joint with the flange edge on the left side of the combustion chamber 4, the acceleration spray pipe 34 on the detection assembly 9 is in butt joint with the flange edge on the right side of the combustion chamber 4, the operator flange-connects the burner 8 and the detection assembly 9 to the flanges on both sides of the combustion chamber 4, respectively, thereby completing the installation work.

It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.

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 an aviation gas turbine's combustion chamber test bench, includes concrete foundation (1) and combustion chamber (4), its characterized in that: the top fixedly connected with installation mechanism (3) of concrete base (1), the left and right both sides of installation mechanism (3) just are located the equal fixed mounting in top of concrete base (1) and have sliding seat (5), two the top of sliding seat (5) is respectively through first mount pad (6) and second mount pad (7) fixedly connected with combustor (8) and detection component (9), installation mechanism (3) includes fixed frame (10), the top fixedly connected with two brackets (11) of fixed frame (10), the outside fixedly connected with of concrete base (1) rear side has stand (12) along vertical direction distribution, the top of stand (12) front side passes through support (13) fixedly connected with hydraulic stem (14) along vertical direction distribution, the output of hydraulic stem (14) runs through in support (13) and extends to the below of support (13) and fixedly connected with grip block (15), sliding seat (5) include two spout (16), two fixedly connected with baffle (17) between the outside of spout (16), fixed mounting has motor (18) on the lateral wall of baffle (17), the output of motor (18) runs through in baffle (17) and extends to between two spout (16) and is connected with movable block (20) through lead screw (19), the top fixedly connected with backup pad (21) of movable block (20), the left and right both sides of backup pad (21) bottom all rotate and are connected with two gyro wheels (22), and gyro wheel (22) and spout (16) looks adaptation.

2. The aircraft gas turbine combustor test rig of claim 1, wherein: the burner (8) comprises a shell (23), a combustion air port (24) is fixedly arranged at the bottom of the shell (23), a positioning plate (25) is fixedly connected on the right side of the combustion air port (24) and on the outer wall of the shell (23), a clapboard (26) is fixedly connected with the right side of the inner wall of the shell (23), a first mounting groove (27) is arranged in the middle of the clapboard (26), a plurality of vent holes (28) are arranged outside the first mounting groove (27) and on the partition plate (26), a plurality of vent holes (28) are distributed in an annular array, the right side of the positioning plate (25) is fixedly connected with a mounting plate (29), a natural gas pipe (31) penetrates through the first mounting groove (27), a flame spray nozzle (32) is arranged at the right end of the natural gas pipe (31), the left side of the outer wall of the natural gas pipe (31) is fixedly connected with a fixing plate (33).

3. The aircraft gas turbine combustor test rig of claim 2, wherein: the detection assembly (9) comprises an accelerating spray pipe (34), a test pipe (35) is fixedly connected to the right side of the accelerating spray pipe (34), and probes (36) penetrate through the top and the bottom of the outer wall of the test pipe (35).

4. The aircraft gas turbine combustor test rig of claim 3, wherein: second mounting groove (30) have been seted up at the middle part of mounting panel (29), the right side of casing (23) runs through in second mounting groove (30) and through locating plate (25) and mounting panel (29) flange joint, the right-hand member of natural gas pipe (31) runs through in first mounting groove (27) and is connected through the left side wall flange of fixed plate (33) with casing (23).

5. The aircraft gas turbine combustor test rig of claim 4, wherein: combustion chamber (4) joint is between grip block (15) and two brackets (11), two the left and right both sides of combustion chamber (4) all are provided with the flange limit, and two flange limits respectively with mounting panel (29) and accelerate spray tube (34) flange joint.

6. The aircraft gas turbine combustor test rig of claim 1, wherein: the concrete foundation (1) left and right sides bottom all sets up ladder groove (2), motor (18) fixed mounting is at the top of ladder groove (2).

7. The aircraft gas turbine combustor test rig of claim 1, wherein: the output of motor (18) passes through shaft coupling and lead screw (19) fixed connection, the both ends of lead screw (19) are rotated with baffle (17) and fixed frame (10) through two bearings respectively and are connected, lead screw (19) run through in movable block (20) and with movable block (20) threaded connection.

8. The aircraft gas turbine combustor test rig of claim 1, wherein: the support (13) is fixedly connected to the top of the front side of the upright post (12) through a tripod, and the support (13) is perpendicular to the upright post (12).