A gas turbine reducer joint structure

Abstract

A gas turbine reducer joint structure belongs to the field of gas turbine structure design. The present invention aims to solve the problems of complex arrangement of the rotational speed measuring device and the lubricating oil pipeline system of the gas turbine, and great difficulty in disassembly, assembly and maintenance. It includes an outer wall, an inner wall and a support housing: a first nozzle, a second nozzle, a third nozzle and a fourth nozzle respectively pass through the outer wall, the inner wall and the support housing in sequence along the radial direction. The fourth nozzle is arranged on the lower side of the axis. A first rotational speed measuring sensor is inserted into the first nozzle, a main oil supply pipe and a second rotational speed measuring sensor are inserted into the second nozzle. A manual barring gear is arranged in the third nozzle. The measuring heads of the first rotational speed measuring sensor and the second rotational speed measuring sensor both face the front shaft of the high-pressure compressor rotor. The main oil supply pipe supplies lubricating oil to the rear support bearing of the low-pressure compressor and the front support bearing of the high-pressure compressor respectively through the lubricating oil passage, realizing the arrangement of the rotational speed measuring device and the lubricating oil pipeline system.

Description

Technical Field

[0001] The present invention belongs to the field of gas turbine structure design, and particularly relates to a reducing joint structure for a gas turbine. Background Art

[0002] A gas turbine is an internal combustion power machine that uses continuously flowing gas as the working medium to drive the impeller to rotate at a high speed, converting the energy of fuel into useful work. It is a rotating impeller type thermal engine. A heavy-duty gas turbine generally includes a low-pressure compressor and a high-pressure compressor arranged coaxially front and back. The low-pressure compressor is used to compress the atmosphere and send it to the high-pressure compressor.

[0003] It is necessary to measure the rotational speed of the respective rotors of the low-pressure compressor and the high-pressure compressor, and at the same time, it is necessary to lubricate the respective rotor support bearings. Therefore, it is necessary to add a rotational speed measuring device and a lubricating oil circuit system to the gas turbine structure. At the same time, it is necessary to seal the rotational speed structure and the oil circuit accordingly. The existing rotational speed measuring device and lubricating oil circuit system of the gas turbine are complex in layout, difficult to disassemble, repair, and occupy a large space. Often, it is necessary to increase the volume of the unit. In addition, arranging a complex oil circuit system on the unit with multiple oil pipes inserted horizontally makes it difficult to set the respective gas seals of the high-pressure and low-pressure compressors. Summary of the Invention

[0004] The purpose of the present invention is to provide a reducing joint structure for a gas turbine to solve the problems of complex layout of the rotational speed measuring device and the lubricating oil circuit system of the gas turbine, and difficult disassembly and repair. The technical solution adopted by the present invention is as follows:

[0005] A reducing joint structure for a gas turbine includes an outer wall, an inner wall, and a support housing:

[0006] The support housing, the inner wall, and the outer wall are coaxially arranged in sequence from inside to outside. The first connecting pipe, the second connecting pipe, the third connecting pipe, and the fourth connecting pipe respectively pass through the outer wall, the inner wall, and the support housing along the radial direction, and are respectively sealedly connected to the outer wall, the inner wall, and the support housing. The second connecting pipe is arranged above the axis, and the fourth connecting pipe is arranged below the axis. A first rotational speed measuring sensor is inserted into the first connecting pipe, a main oil supply pipe and a second rotational speed measuring sensor are inserted into the second connecting pipe, a manual barring device is arranged in the third connecting pipe, and the measuring heads of the first rotational speed measuring sensor and the second rotational speed measuring sensor both face the front shaft part of the high-pressure rotor;

[0007] An outlet guide vane assembly of the low-pressure compressor is arranged at the front end of the air flow passage formed between the outer wall and the inner wall, and an inlet guide vane assembly of the high-pressure compressor is arranged at the end of the air flow passage;

[0008] A decompression chamber is formed between the inner wall and the support housing. The first gland and the second gland which are sleeved inside and outside are respectively fixed on the outer side of the front side wall of the decompression chamber. The first gland is rotationally sealed with the rear journal of the low-pressure rotor through a comb structure. The second gland is rotationally sealed with the end turntable of the low-pressure compressor through a comb structure. A through hole is provided on the front side wall of the decompression chamber. The through hole is arranged between the first gland and the second gland. The inner cavity of the low-pressure rotor is communicated with the decompression chamber through the through hole;

[0009] An irregular-shaped sleeve is provided at the front part of the inner circumference of the support housing. The rear support housing of the low-pressure compressor is connected to the irregular-shaped sleeve. Annular grooves are provided on the outer circumference of the rear support housing and the inner circumference of the irregular-shaped sleeve. The two annular grooves are connected and combined to form an oil distribution channel. The irregular-shaped sleeve is machined with a first oil passage hole. One end of the first oil passage hole is communicated with the oil distribution channel, and the other end of the first oil passage hole is connected to the inner end of the main oil supply pipe;

[0010] The outer ring bushing is sleeved on the rear support bearing of the low-pressure compressor. A first annular oil gap is formed between the outer circumference of the outer ring bushing and the inner circumference of the rear support housing. The rear support housing is provided with a number of second oil passage holes arranged circumferentially and a number of third oil passage holes arranged circumferentially. The first annular oil gap is communicated with the oil distribution channel through a number of second oil passage holes. The rear support housing is provided with a first injector. The first injector is annular. The first injector is machined with an annular fourth oil passage hole. The oil distribution channel is communicated with the outer end of the fourth oil passage hole through a number of third oil passage holes. The inner end of the fourth oil passage hole is provided with a number of nozzle structures facing the rear support bearing. The bottom of the rear support housing is provided with a first oil drain passage hole communicating the front and rear sides thereof. The inner ring of the rear support bearing, the low-pressure oil baffle ring and the low-pressure support limit bushing are all sleeved on the rear shaft part of the low-pressure rotor. The front end of the inner ring of the rear support bearing abuts against the shaft shoulder of the rear shaft part of the low-pressure rotor through the low-pressure oil baffle ring and the low-pressure support limit bushing in sequence. The rear end of the inner ring of the rear support bearing abuts against the low-pressure end locking nut. The low-pressure end locking nut is in threaded cooperation with the rear shaft part of the low-pressure rotor. The low-pressure support limit bushing is provided with a first sealing ring. The outer end of the first sealing end cover is connected to the front end of the rear support housing. The inner end of the first sealing end cover is rotationally sealed with the rear shaft part of the low-pressure rotor through the first sealing ring;

[0011] The front support housing of the high-pressure compressor and the oil circuit sleeve are sleeved and arranged from the inside to the outside. The front ends of the front support housing and the oil circuit sleeve are respectively connected to the rear end of the support housing. The front support housing is connected to the outer ring of the front support bearing of the high-pressure compressor. The inner ring of the front support bearing, the high-pressure oil baffle ring, and the high-pressure support limit bushing are all sleeved on the front shaft part of the high-pressure rotor. The rear end of the inner ring of the front support bearing abuts against the shaft shoulder of the front shaft part of the high-pressure rotor through the high-pressure oil baffle ring and the high-pressure support limit bushing in sequence. The front end of the inner ring of the front support bearing abuts against the high-pressure end locking nut. The high-pressure end locking nut is in threaded fit with the front shaft part of the high-pressure rotor. A number of fifth oil circuit holes are machined on the high-pressure oil baffle ring and arranged in a circle. A number of sixth oil circuit holes are machined on the front shaft part of the high-pressure rotor and arranged in a circle. An oil guiding ring is provided on the front support housing. A number of second injectors arranged in a circle are respectively connected to the oil guiding ring. A seventh oil circuit hole is machined on the second injector. The fourth oil circuit hole is communicated with one end of a number of seventh oil circuit holes through a number of first sub-feed oil pipes one by one. The other end of the seventh oil circuit hole is provided with a nozzle structure facing the sixth oil circuit hole and the front support bearing. The other end of the sixth oil circuit hole is connected to the inner hole of the front support bearing. The balls and the inner hole of the front support bearing are connected through a number of fifth oil circuit holes. A second oil drain hole communicating the front and rear sides of the front support housing is provided at the bottom of the front support housing. A second sealing ring is provided on the high-pressure support limit bushing. The outer end of the second sealing end cover is connected to the rear end of the oil circuit sleeve. The inner end of the second sealing end cover is rotationally sealed with the front shaft part of the high-pressure rotor through the second sealing ring. The first sealing end cover, the rear support housing, the special-shaped sleeve, the support housing, the oil circuit sleeve, and the second sealing end cover together form an oil cavity.

[0012] Further, two damping sealing rings are provided between the outer periphery of the front support housing and the inner periphery of the oil circuit sleeve. A second annular oil gap is formed between the front support housing, the oil circuit sleeve, and the two damping sealing rings. An eighth oil circuit hole is machined on the oil circuit sleeve. The oil distribution channel is communicated with the second annular oil gap through a second sub-feed oil pipe and the eighth oil circuit hole in sequence.

[0013] Further, a threaded structure is provided at the end of the inner periphery of the outer ring bushing, and the threaded structure protrudes from the rear end face of the rear support bearing. The outer periphery of the adjusting ring is matched with the threaded structure. An end gap is formed between the rear end of the adjusting ring and the front end of the first injector. The front end of the outer ring bushing abuts against the front end of the special-shaped sleeve to close the front end of the first annular oil gap. The rear end of the first annular oil gap is connected to the end gap.

[0014] Further, a labyrinth seal pressing sleeve is sleeved on the outside of the oil circuit sleeve. The front end of the labyrinth seal pressing sleeve is connected to the rear end of the support housing. The rear end of the labyrinth seal pressing sleeve is rotationally sealed with the labyrinth seal bushing through a comb tooth seal structure.

[0015] Furthermore, a bump fixing frame structure is provided at the end of the special-shaped sleeve. A fixing hole is provided on the bump fixing frame structure, and the probe of the second rotational speed measurement sensor is fixed in cooperation with the fixing hole.

[0016] Compared with the prior art, the beneficial effects of the present invention are as follows:

[0017] 1. The present invention is used to connect the low-pressure compressor and the high-pressure compressor of a gas turbine, making full use of the space and structure between the low-pressure compressor and the high-pressure compressor to measure the rotational speed of the high-pressure compressor and lubricate and supply oil to the front support bearing of the high-pressure compressor and the rear support bearing of the low-pressure compressor.

[0018] 2. The oil distribution channel is sequentially communicated with the second annular oil gap through the second sub-oil supply pipe and the eighth oil passage hole. The engine oil enters the second annular oil gap and can be used as a damper, which can effectively reduce the vibration transmitted from the front support bearing to the casing. At the same time, a labyrinth seal bush is provided to reduce the temperature in the oil chamber.

[0019] 3. The present invention can effectively seal the engine oil in the oil chamber and discharge it from the fourth connecting pipe of the reduced-diameter joint structure. At the same time, it can cooperate with the high-pressure compressor rotor and the low-pressure compressor rotor for gas sealing. Description of the Drawings

[0020] Figure 1 is a radial sectional view of the second connecting pipe of the present invention;

[0021] Figure 2 is a schematic diagram of the oil supply and lubrication structure of the rear support bearing of the low-pressure compressor;

[0022] Figure 3 is a schematic diagram of the oil supply and lubrication structure of the front support bearing of the high-pressure compressor;

[0023] Figure 4 is a front sectional view of the present invention.

[0024] In the figure: 1 - outlet guide vane assembly, 2 - rear support housing, 3 - front support housing, 4 - inlet guide vane assembly, 5 - second rotational speed measurement sensor, 6 - outer wall, 7 - inner wall, 8 - support housing, 9 - second gland, 10 - first gland, 11 - second nozzle, 12 - bump fixing frame structure, 13 - main oil supply pipe, 14 - oil distribution channel, 15 - first oil passage, 16 - first sub - oil supply pipe, 17 - second oil passage, 18 - outer ring bushing, 19 - first annular oil clearance, 20 - first sealing end cover, 21 - first sealing ring, 22 - end clearance, 23 - adjusting ring, 24 - first injector, 25 - rear support bearing, 26 - special - shaped sleeve, 27 - sixth oil passage, 28 - fifth oil passage, 29 - high - pressure support limit bushing, 30 - high - pressure oil baffle, 31 - labyrinth seal bushing, 32 - second sealing ring, 33 - second sealing end cover, 34 - damping sealing ring, 35 - front support bearing, 36 - labyrinth seal bushing, 37 - eighth oil passage, 38 - oil passage sleeve, 39 - third oil passage, 40 - low - pressure support limit bushing, 41 - oil guiding ring, 42 - second injector, 43 - first nozzle, 44 - rear journal of low - pressure rotor, 45 - third nozzle, 46 - fourth nozzle, 47 - rear shaft part of low - pressure rotor, 48 - low - pressure oil baffle, 49 - low - pressure end locking nut, 50 - high - pressure end locking nut, 51 - front shaft part of high - pressure rotor, 52 - front journal of high - pressure rotor, 53 - second sub - oil supply pipe, 54 - fourth oil passage, 55 - seventh oil passage, 56 - first oil drain hole, 57 - second oil drain hole. Detailed implementation manners

[0025] To make the objectives, technical solutions and advantages of the present invention clearer and more understandable, the present invention will be described below through specific embodiments shown in the drawings. However, it should be understood that these descriptions are merely exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, the descriptions of well - known structures and technologies are omitted to avoid unnecessarily confusing the concepts of the present invention.

[0026] The connections mentioned in the present invention are divided into fixed connections and detachable connections. The fixed connection is an inseparable connection, including but not limited to conventional fixed connection methods such as flanging connection, riveting connection, bonding connection and welding connection, etc. The detachable connection includes but not limited to conventional disassembly methods such as bolt connection, snap connection, pin connection and hinge connection, etc. When the specific connection method is not clearly defined, it is defaulted that at least one connection method can be found among the existing connection methods to achieve this function, and those skilled in the art can select according to their needs. For example: for the fixed connection, welding connection is selected; for the detachable connection, bolt connection is selected.

[0027] The present invention will be further described in detail below with reference to the drawings. The following embodiments are explanations of the present invention, and the present invention is not limited to the following embodiments.

[0028] Embodiment: As Figures 1-4 shown, a gas turbine reducer joint structure includes an outer wall 6, an inner wall 7, and a support housing 8:

[0029] The support housing 8, the inner wall 7, and the outer wall 6 are coaxially arranged in sequence from the inside to the outside. The first nozzle 43, the second nozzle 11, the third nozzle 45, and the fourth nozzle 46 respectively pass through the outer wall 6, the inner wall 7, and the support housing 8 along the radial direction, and are respectively and hermetically connected to the outer wall 6, the inner wall 7, and the support housing 8. The first nozzle 43 is arranged on one side below the axis, the second nozzle 11 and the third nozzle 45 are respectively arranged on both sides above the axis, the fourth nozzle 46 is arranged on the lower side of the axis, the fourth nozzle 46, the first nozzle 43, the second nozzle 11, and the third nozzle 45 are arranged at intervals of 72° in sequence. A first rotational speed measurement sensor is inserted into the first nozzle 43, a main oil supply pipe 13 and a second rotational speed measurement sensor 5 are inserted into the second nozzle 11, a manual barring device is arranged in the third nozzle 45, and the probes of the first rotational speed measurement sensor and the second rotational speed measurement sensor 5 both face the front shaft part 51 of the high-pressure rotor. The fourth nozzle 46 is used for draining oil;

[0030] At the front end of the air flow passage formed between the outer wall 6 and the inner wall 7, there is an outlet guide vane assembly 1 of the low-pressure compressor, and at the end of the air flow passage, there is an inlet guide vane assembly 4 of the high-pressure compressor;

[0031] A decompression chamber is formed between the inner wall 7 and the support housing 8. The first gland 10 and the second gland 9 which are sleeved inside and outside are respectively fixed on the outer side of the front side wall of the decompression chamber. The first gland 10 is rotationally sealed with the rear journal 44 of the low-pressure rotor through a labyrinth structure, and the second gland 9 is rotationally sealed with the end disk of the low-pressure compressor through a labyrinth structure. A through hole is arranged on the front side wall of the decompression chamber, and the through hole is arranged between the first gland 10 and the second gland 9. The inner cavity of the low-pressure rotor is communicated with the decompression chamber through the through hole;

[0032] At the front part of the inner circumference of the support housing 8, there is a special-shaped sleeve 26. The rear support housing 2 of the low-pressure compressor is connected to the special-shaped sleeve 26. Annular grooves are respectively arranged on the outer circumference of the rear support housing 2 and the inner circumference of the special-shaped sleeve 26, and the two annular grooves are connected and combined to form an oil distribution channel 14. A first oil passage hole 15 is processed on the special-shaped sleeve 26. One end of the first oil passage hole 15 is communicated with the oil distribution channel 14, and the other end of the first oil passage hole 15 is connected to the inner end of the main oil supply pipe 13;

[0033] The outer ring bushing 18 is sleeved on the outer ring of the rear support bearing 25 of the low-pressure compressor. A first annular oil gap 19 is formed between the outer circumference of the outer ring bushing 18 and the inner circumference of the rear support housing 2. The rear support housing 2 is provided with a number of second oil passage holes 17 arranged circumferentially and a number of third oil passage holes 39 arranged circumferentially. The first annular oil gap 19 is communicated with the oil distribution passage 14 through a number of second oil passage holes 17. The rear support housing 2 is provided with a first injector 24. The first injector 24 is annular. An annular fourth oil passage hole 54 is machined on the first injector 24. The oil distribution passage 14 is communicated with the outer end of the fourth oil passage hole 54 through a number of third oil passage holes 39. The inner end of the fourth oil passage hole 54 is provided with a number of nozzle structures facing the rear support bearing 25. The bottom of the rear support housing 2 is provided with a first oil drain passage 56 communicating the front and rear sides thereof. The inner ring of the rear support bearing 25, the low-pressure oil baffle 48 and the low-pressure support limit bushing 40 are all sleeved on the rear shaft portion 47 of the low-pressure rotor. The front end of the inner ring of the rear support bearing 25 abuts against the shaft shoulder of the rear shaft portion 47 of the low-pressure rotor through the low-pressure oil baffle 48 and the low-pressure support limit bushing 40 in sequence. The rear end of the inner ring of the rear support bearing 25 abuts against the low-pressure end locking nut 49. The low-pressure end locking nut 49 is in threaded cooperation with the rear shaft portion 47 of the low-pressure rotor. The low-pressure support limit bushing 40 is provided with a first sealing ring 21. The outer end of the first sealing end cover 20 is connected to the front end of the rear support housing 2. The inner end of the first sealing end cover 20 is rotationally sealed with the rear shaft portion 47 of the low-pressure rotor through the first sealing ring 21;

[0034] The front support housing 3 of the high-pressure compressor and the oil circuit sleeve 38 are sleeved and arranged from the inside to the outside. The front ends of the front support housing 3 and the oil circuit sleeve 38 are respectively connected to the rear end of the support housing 8. The front support housing 3 is connected to the outer ring of the front support bearing 35 of the high-pressure compressor. The inner ring of the front support bearing 35, the high-pressure oil retaining ring 30, and the high-pressure support limit bushing 29 are all sleeved on the front shaft portion 51 of the high-pressure rotor. The rear end of the inner ring of the front support bearing 35 abuts against the shoulder of the front shaft portion 51 of the high-pressure rotor through the high-pressure oil retaining ring 30 and the high-pressure support limit bushing 29 in sequence. The front end of the inner ring of the front support bearing 35 abuts against the high-pressure end locking nut 50. The high-pressure end locking nut 50 is in threaded cooperation with the front shaft portion 51 of the high-pressure rotor. A number of fifth oil passage holes 28 are machined on the high-pressure oil retaining ring 30 in a circumferential arrangement. A number of sixth oil passage holes 27 are machined on the front shaft portion 51 of the high-pressure rotor in a circumferential arrangement. An oil guide ring 41 is provided on the front support housing 3. A number of second injectors 42 arranged in a circumferential manner are respectively connected to the oil guide ring 41. A seventh oil passage hole 55 is machined on the second injector 42. The fourth oil passage hole 54 is communicated with one end of a number of seventh oil passage holes 55 through a number of first sub-feed oil pipes 16 in a one-to-one correspondence. The other end of the seventh oil passage hole 55 is provided with a nozzle structure facing the sixth oil passage hole 27 and the front support bearing 35. The other end of the sixth oil passage hole 27 is connected to the inner hole of the front support bearing 35. The balls and the inner hole of the front support bearing 35 are connected through a number of fifth oil passage holes 28. A second oil drain passage hole 57 communicating the front and rear sides thereof is provided at the bottom of the front support housing 3. A second sealing ring 32 is provided on the high-pressure support limit bushing 29. The outer end of the second sealing end cover 33 is connected to the rear end of the oil circuit sleeve 38. The inner end of the second sealing end cover 33 is rotationally sealed with the front shaft portion 51 of the high-pressure rotor through the second sealing ring 32. The first sealing end cover 20, the rear support housing 2, the special-shaped sleeve 26, the support housing 8, the oil circuit sleeve 38, and the second sealing end cover 33 together form an oil cavity.

[0035] Two damping sealing rings 34 are provided between the outer circumference of the front support housing 3 and the inner circumference of the oil circuit sleeve 38. A second annular oil gap is formed among the front support housing 3, the oil circuit sleeve 38, and the two damping sealing rings 34. An eighth oil passage hole 37 is machined on the oil circuit sleeve 38. The oil distribution passage 14 is communicated with the second annular oil gap through the second sub-feed oil pipe 53 and the eighth oil passage hole 37 in sequence.

[0036] The inner end of the outer ring bushing 18 is provided with a threaded structure, and the threaded structure protrudes from the rear end face of the rear support bearing 25. The outer circumference of the adjusting ring 23 is matched with the threaded structure. An end gap 22 is formed between the rear end of the adjusting ring 23 and the front end of the first injector 24. The front end of the outer ring bushing 18 abuts against the front end of the special-shaped sleeve 26 to close the front end of the first annular oil gap 19. The rear end of the first annular oil gap 19 is connected to the end gap 22. By screwing the adjusting ring 23, the end gap 22 can be adjusted to control the amount of engine oil flowing out of the first annular oil gap 19.

[0037] A labyrinth seal pressing sleeve 36 is sleeved outside the oil passage sleeve 38. The front end of the labyrinth seal pressing sleeve 36 is connected to the rear end of the support housing 8. The front end turntable of the high-pressure compressor rotor is connected to the high-pressure rotor front journal 52 through a labyrinth seal bushing 31. The rear end of the labyrinth seal pressing sleeve 36 is rotationally sealed with the labyrinth seal bushing 31 through a comb tooth seal structure.

[0038] The end of the special-shaped sleeve 26 is provided with a convex block fixing frame structure 12, and a fixing hole is formed in the convex block fixing frame structure 12. The probe of the second rotational speed measuring sensor 5 is fixedly fitted with the fixing hole.

[0039] Both the first rotational speed measuring sensor and the second rotational speed measuring sensor 5 are used to measure the rotational speed of the high-pressure compressor rotor. The main oil supply pipe 13 is used to supply oil for lubrication to the rear support bearing 25 of the low-pressure compressor and the front support bearing 35 of the high-pressure compressor. Engine oil sequentially passes through the main oil supply pipe 13, the first oil passage hole 15, the oil distribution channel 14 and several second oil passage holes 17 to supply oil to the first annular oil gap 19 between the rear support bearing 25 and the outer ring bushing 18, and sequentially passes through the oil distribution channel 14, several third oil passage holes 39 and the fourth oil passage hole 54 to spray the engine oil onto the rollers of the rear support bearing 25. The engine oil between the rear support bearing 25 and the first sealing end cover 20 can return to the rear side of the rear support bearing 25 through the first oil drain hole 56 and is discharged from the reducing joint structure through the fourth connecting pipe 46.

[0040] The annular fourth oil passage hole 54 sequentially sprays the engine oil onto the rollers of the front support bearing 35 and several sixth oil passage holes 27 through several first sub-oil supply pipes 16 and several seventh oil passage holes 55. The engine oil lubricates the inner circumference of the inner ring of the front support bearing 35 through several sixth oil passage holes 27. Several fifth oil passage holes 28 are used to discharge the engine oil on the inner circumference of the inner ring of the front support bearing 35 into the cavity between the front support bearing 35 and the second sealing end cover 33, then return to the front end of the front support bearing 35 through the second oil drain hole 57 and is discharged from the reducing joint structure through the fourth connecting pipe 46.

[0041] The present invention is used to connect the low-pressure compressor and the high-pressure compressor of a gas turbine, and makes full use of the space and structure between the low-pressure compressor and the high-pressure compressor to measure the rotational speed of the high-pressure compressor and lubricate and supply oil to the front support bearing 35 of the high-pressure compressor and the rear support bearing 25 of the low-pressure compressor.

[0042] The oil distribution channel 14 is sequentially communicated with the second annular oil gap through the second sub-feed oil pipe 53 and the eighth oil passage hole 37. When the engine oil enters the second annular oil gap, it can act as a damper, effectively reducing the vibration transmitted from the front support bearing 35 to the casing. At the same time, a labyrinth seal bushing 36 is provided to reduce the temperature in the oil chamber.

[0043] The present invention can effectively seal the engine oil in the oil chamber and discharge it from the reduced-diameter joint structure through the fourth connecting pipe 46. At the same time, it can cooperate with the high-pressure compressor rotor and the low-pressure compressor rotor for gas sealing.

[0044] The above embodiments are only exemplary descriptions of the present invention and do not limit its protection scope. Those skilled in the art can also make partial changes to it as long as they do not exceed the spirit of the present invention, and they are all within the protection scope of the present invention.

Claims

1. A structure of a reducing joint for a gas turbine, characterized in that: it includes an outer wall (6), an inner wall (7) and a support housing (8): The support housing (8), the inner wall (7) and the outer wall (6) are coaxially arranged from the inside to the outside in sequence. The first nozzle (43), the second nozzle (11), the third nozzle (45) and the fourth nozzle (46) respectively pass through the outer wall (6), the inner wall (7) and the support housing (8) along the radial direction, and are respectively and hermetically connected to the outer wall (6), the inner wall (7) and the support housing (8). The second nozzle (11) is arranged above the axis, the fourth nozzle (46) is arranged below the axis. A first rotational speed measurement sensor penetrates into the first nozzle (43), a main fuel supply pipe (13) and a second rotational speed measurement sensor (5) penetrate into the second nozzle (11), a manual barring gear is arranged in the third nozzle (45), and the measuring heads of the first rotational speed measurement sensor and the second rotational speed measurement sensor (5) both face the front shaft part (51) of the high-pressure rotor; An outlet guide vane assembly (1) of a low-pressure compressor is arranged at the front end of an air flow passage formed between the outer wall (6) and the inner wall (7), and an inlet guide vane assembly (4) of a high-pressure compressor is arranged at the end of the air flow passage; A decompression chamber is formed between the inner wall (7) and the support housing (8). The first gland (10) and the second gland (9) which are sleeved with each other are respectively fixed on the outer side of the front side wall of the decompression chamber. The first gland (10) and the rear journal of the low-pressure rotor (44) are rotationally sealed through a labyrinth structure, and the second gland (9) and the end turntable of the low-pressure compressor are rotationally sealed through a labyrinth structure. A through hole is arranged on the front side wall of the decompression chamber, and the through hole is arranged between the first gland (10) and the second gland (9). The inner cavity of the low-pressure rotor is communicated with the decompression chamber through the through hole; A special-shaped sleeve (26) is arranged at the front part of the inner circumference of the support housing (8). The rear support housing (2) of the low-pressure compressor is connected to the special-shaped sleeve (26). Annular grooves are respectively arranged on the outer circumference of the rear support housing (2) and the inner circumference of the special-shaped sleeve (26), and the two annular grooves are connected and combined to form an oil distribution channel (14). A first oil passage hole (15) is machined on the special-shaped sleeve (26), one end of the first oil passage hole (15) is communicated with the oil distribution channel (14), and the other end of the first oil passage hole (15) is connected to the inner end of the main fuel supply pipe (13); The outer ring bushing (18) is sleeved on the rear support bearing (25) of the low-pressure compressor. A first annular oil gap (19) is formed between the outer periphery of the outer ring bushing (18) and the inner periphery of the rear support housing (2). The rear support housing (2) is provided with a number of second oil passage holes (17) arranged circumferentially and a number of third oil passage holes (39) arranged circumferentially. The first annular oil gap (19) is communicated with the oil distribution passage (14) through a number of second oil passage holes (17). The rear support housing (2) is provided with a first injector (24). The first injector (24) is annular. An annular fourth oil passage hole (54) is machined on the first injector (24). The oil distribution passage (14) is communicated with the outer end of the fourth oil passage hole (54) through a number of third oil passage holes (39). The inner end of the fourth oil passage hole (54) is provided with a number of nozzle structures facing the rear support bearing (25). The bottom of the rear support housing (2) is provided with a first oil drain passage (56) communicating the front and rear sides thereof. The inner ring of the rear support bearing (25), the low-pressure oil baffle ring (48) and the low-pressure support limit bushing (40) are all sleeved on the rear shaft portion (47) of the low-pressure rotor. The front end of the inner ring of the rear support bearing (25) abuts against the shoulder of the rear shaft portion (47) of the low-pressure rotor through the low-pressure oil baffle ring (48) and the low-pressure support limit bushing (40) in sequence. The rear end of the inner ring of the rear support bearing (25) abuts against the low-pressure end locking nut (49). The low-pressure end locking nut (49) is in threaded fit with the rear shaft portion (47) of the low-pressure rotor. The low-pressure support limit bushing (40) is provided with a first sealing ring (21). The outer end of the first sealing end cover (20) is connected to the front end of the rear support housing (2). The inner end of the first sealing end cover (20) is rotationally sealed with the rear shaft portion (47) of the low-pressure rotor through the first sealing ring (21); The front support housing (3) of the high-pressure compressor and the oil circuit sleeve (38) are sleeved and arranged from inside to outside. The front ends of the front support housing (3) and the oil circuit sleeve (38) are respectively connected to the rear end of the support housing (8). The front support housing (3) is connected to the outer ring of the front support bearing (35) of the high-pressure compressor. The inner ring of the front support bearing (35), the high-pressure oil baffle ring (30), and the high-pressure support limit bushing (29) are all sleeved on the front shaft part (51) of the high-pressure rotor. The rear end of the inner ring of the front support bearing (35) abuts against the shaft shoulder of the front shaft part (51) of the high-pressure rotor through the high-pressure oil baffle ring (30) and the high-pressure support limit bushing (29) in sequence. The front end of the inner ring of the front support bearing (35) abuts against the high-pressure end locking nut (50). The high-pressure end locking nut (50) is in threaded cooperation with the front shaft part (51) of the high-pressure rotor. A number of fifth oil passage holes (28) are machined on the high-pressure oil baffle ring (30) and arranged in a circle. A number of sixth oil passage holes (27) are machined on the front shaft part (51) of the high-pressure rotor and arranged in a circle. An oil guide ring (41) is provided on the front support housing (3). A number of second injectors (42) arranged in a circle are respectively connected to the oil guide ring (41). A seventh oil passage hole (55) is machined on the second injector (42). The fourth oil passage hole (54) is communicated with one end of a number of seventh oil passage holes (55) through a number of first sub-feed oil pipes (16) one by one. The other end of the seventh oil passage hole (55) is provided with a nozzle structure facing the sixth oil passage hole (27) and the front support bearing (35). The other end of the sixth oil passage hole (27) is connected to the inner hole of the front support bearing (35). The balls and the inner hole of the front support bearing (35) are connected through a number of fifth oil passage holes (28). A second oil drain hole (57) communicating the front and rear sides is provided at the bottom of the front support housing (3). A second sealing ring (32) is provided on the high-pressure support limit bushing (29). The outer end of the second sealing end cover (33) is connected to the rear end of the oil circuit sleeve (38). The inner end of the second sealing end cover (33) is rotationally sealed with the front shaft part (51) of the high-pressure rotor through the second sealing ring (32). The first sealing end cover (20), the rear support housing (2), the special-shaped sleeve (26), the support housing (8), the oil circuit sleeve (38), and the second sealing end cover (33) together form an oil cavity.

2. The structure of a gas turbine reducing joint according to claim 1, wherein: There are two damping sealing rings (34) between the outer circumference of the front support housing (3) and the inner circumference of the oil circuit sleeve (38). A second annular oil gap is formed among the front support housing (3), the oil circuit sleeve (38), and the two damping sealing rings (34). An eighth oil passage hole (37) is machined on the oil circuit sleeve (38). The oil distribution channel (14) is communicated with the second annular oil gap through the second sub-feed oil pipe (53) and the eighth oil passage hole (37) in sequence.

3. The structure of a gas turbine reducing joint according to claim 1, wherein: The inner end of the outer ring bushing (18) is provided with a threaded structure, and the threaded structure protrudes from the rear end face of the rear support bearing (25). The outer circumference of the adjusting ring (23) is matched with the threaded structure. An end gap (22) is formed between the rear end of the adjusting ring (23) and the front end of the first injector (24). The front end of the outer ring bushing (18) abuts against the front end of the special-shaped sleeve (26) to close the front end of the first annular oil gap (19), and the rear end of the first annular oil gap (19) is connected to the end gap (22).

4. A gas turbine reducer joint structure according to claim 1, characterized in that: A labyrinth seal gland (36) is sleeved outside the oil circuit sleeve (38). The front end of the labyrinth seal gland (36) is connected to the rear end of the support housing (8), and the rear end of the labyrinth seal gland (36) is rotationally sealed with the labyrinth seal bushing (31) through a comb tooth seal structure.

5. A gas turbine reducer joint structure according to any one of claims 1-4, characterized in that: The end of the special-shaped sleeve (26) is provided with a convex block fixing frame structure (12), and a fixing hole is formed in the convex block fixing frame structure (12). The probe of the second rotational speed measurement sensor (5) is fixedly fitted with the fixing hole.

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