CN211343133U

CN211343133U - Miniature gas turbine with high combustion efficiency

Info

Publication number: CN211343133U
Application number: CN201922417641.8U
Authority: CN
Inventors: 靳普
Original assignee: Zhiyue Tengfeng Technology Group Co ltd
Current assignee: Liu Muhua
Priority date: 2019-12-27
Filing date: 2019-12-27
Publication date: 2020-08-25
Anticipated expiration: 2029-12-27

Abstract

The utility model provides a high combustion efficiency's miniature gas turbine, include: a compressor, a turbine and a combustor assembly; the combustion chamber assembly comprises a combustion chamber, an air inlet cavity, an air inlet channel and an exhaust channel, wherein the air inlet cavity comprises an internal air inlet cavity and an external air inlet cavity which are integrated, the air outlet end of the external air inlet cavity is communicated with the air inlet end of the internal air inlet cavity, the air inlet end of the external air inlet cavity is communicated with the air inlet channel, and the air inlet channel is communicated with the air outlet end of the compressor; the combustion chamber is arranged between the internal air inlet cavity and the external air inlet cavity, and an air outlet of the combustion chamber is communicated with the exhaust channel; the impeller of the compressor is coaxially connected with the turbine through a rotating shaft, and the rim of the turbine extends into the exhaust channel. The utility model discloses compact structure need not to use the air-blower air feed during the use, and can guarantee through the reasonable setting to the combustion chamber structure that gas turbine has higher heat exchange efficiency.

Description

Miniature gas turbine with high combustion efficiency

Technical Field

The utility model relates to a heating equipment technical field especially relates to a miniature gas turbine of high combustion efficiency.

Background

In the primary energy of China, coal accounts for 94%, which is the main characteristic of natural resources in China, the national situation determines in a very long history stage, and most cities in China still have to rely on coal heating. However, in the central heating area, due to the large population density, emissions of heating fuel overlap with other pollution sources every heating season, so that the haze condition of the heating area frosts on snow. Therefore, clean heating is a hot problem concerned by all circles of our society at present.

At present, gas heating is a main clean heating mode. However, the existing gas heating equipment has the problems of large volume and large occupied space, and on the other hand, the existing gas heating equipment needs to use a blower for supplying gas in the working process, needs to be maintained and repaired frequently, and wastes manpower; meanwhile, the existing gas heating equipment is difficult to ensure the efficient heat exchange efficiency.

SUMMERY OF THE UTILITY MODEL

In order to solve the technical problem, an object of the present invention is to provide a micro gas turbine with high combustion efficiency, which has the advantages of compact structure, no need of using air blower for air supply, and makes the gas turbine have higher heat exchange efficiency through reasonable arrangement of the combustion chamber.

The technical scheme of the utility model as follows:

a high combustion efficiency micro gas turbine comprising: a compressor, a turbine and a combustor assembly;

the combustion chamber assembly comprises a combustion chamber, an air inlet cavity, an air inlet channel and an exhaust channel, wherein the air inlet cavity comprises an internal air inlet cavity and an external air inlet cavity which are integrated, the air outlet end of the external air inlet cavity is communicated with the air inlet end of the internal air inlet cavity, the air inlet end of the external air inlet cavity is communicated with the air inlet channel, and the air inlet channel is communicated with the air outlet end of the compressor;

the combustion chamber is arranged between the internal air inlet cavity and the external air inlet cavity, and an air outlet of the combustion chamber is communicated with the exhaust channel;

the impeller of the compressor is coaxially connected with the turbine through a rotating shaft, and the rim of the turbine extends into the exhaust channel.

Furthermore, the internal air inlet cavity and the external air inlet cavity are both annular, and an air outlet end at the tail end of the external air inlet cavity is communicated with an air inlet end of the internal air inlet cavity in a winding manner and surrounds the combustion chamber;

and air holes are distributed on the radial inner wall and the radial outer wall of the combustion chamber, and the combustion chamber is separated from the inner air inlet cavity and the outer air inlet cavity by the radial inner wall and the radial outer wall respectively.

Further, the exhaust passage is annular and is arranged around the axis of the rotating shaft, and the air outlet of the combustion chamber is arranged at the front part of the exhaust passage and at the front side of the turbine.

Furthermore, support ribs are arranged in the combustion chamber, the air inlet cavity, the exhaust channel and the air inlet channel.

Further, the turbine is an axial flow turbine, and a rim of the axial flow turbine is perpendicular to the exhaust channel.

Further, the air inlet channel surrounds the rotating shaft, and the air inlet cavity, the combustion chamber and the exhaust channel are all arranged around the turbine.

Further, the diameter of the combustion chamber close to the combustion chamber air outlet is gradually reduced.

Further, the compressor also comprises an air inlet cylinder and a rear end cover which are integrated; the impeller is sleeved and fixed at the front end of the rotating shaft;

the front fixing end cover is sleeved on the rotating shaft and close to the impeller, a gas outlet channel of the gas compressor is formed in a gap between the front fixing end cover and the rear end cover, and the gas outlet channel is communicated with the gas inlet cylinder and a gas inlet channel of the combustion chamber assembly.

Furthermore, the front end of the inner side wall of the air inlet channel of the combustion chamber assembly is fixed at the edge of the front fixed end cover, and the outer side wall of the air inlet channel of the combustion chamber assembly is fixed at the edge of the rear end cover;

and a rear fixed end cover is sleeved on the rotating shaft and close to the turbine, and the combustor component is close to a connecting arm of the rear fixed end cover and is fixedly connected with the rear fixed end cover.

Further, sealing elements are arranged between the turbine wheel rim and the exhaust channel, between the rotating shaft and the front fixed end cover, between the rotating shaft and the rear fixed end cover and between the turbine and the rear fixed end cover for sealing.

Compared with the prior art, the utility model discloses following beneficial effect has:

the micro gas turbine with high combustion efficiency provided by the utility model has compact structure and small occupied space, and can ensure that the pressure of the fuel gas supplied to the combustion chamber is automatically matched with the pressure of air, and is irrelevant to the rotation speed of the rotor component; meanwhile, the combustion chamber of the utility model is structurally designed, the air inlet cavity is in a C shape and surrounds the combustion chamber, the annular inner air inlet cavity and the annular outer air inlet cavity are connected in a winding manner, an air inlet path is increased, and due to the high temperature in the combustion chamber, gas in each part of the air inlet cavity can be preheated through heat exchange, so that the reaction efficiency is improved; on the other hand, air can be fed in all directions of the wall of the combustion chamber, so that the combustion reaction is more sufficient; the combustion chamber outlet is arranged on the front side of the turbine, the shaft length of the rotating shaft is shorter, the rotor rotates more stably, and the size of the whole machine is smaller.

Drawings

FIG. 1 is a schematic view of an embodiment of a high combustion efficiency micro gas turbine according to the present invention;

FIG. 2 is a schematic structural view of a second embodiment of the high combustion efficiency micro gas turbine of the present invention;

FIG. 3 is a schematic diagram of a third embodiment of a high combustion efficiency micro gas turbine according to the present invention;

FIG. 4 is a schematic diagram of a fourth embodiment of a high combustion efficiency micro gas turbine according to the present invention;

FIG. 5 is a schematic structural diagram of an embodiment of a micro gas turbine with high combustion efficiency according to the present invention;

FIG. 6 is a schematic view of a sixth embodiment of a high combustion efficiency micro gas turbine according to the present invention;

FIG. 7 is a schematic view of a seventh embodiment of a high combustion efficiency micro gas turbine according to the present invention;

FIG. 8 is an eight schematic structural view of an embodiment of a high combustion efficiency micro gas turbine according to the present invention;

FIG. 9 is a schematic view showing the construction of a boiler-heating micro gas turbine heating apparatus;

FIG. 10 is a schematic view showing a construction of a micro gas turbine heating apparatus for electric heater heating;

FIG. 11 is a schematic diagram of a combined heat and power micro gas turbine heating plant;

FIG. 12 is a schematic view of a rotor structure of a motor when an electric heater or a cogeneration mode is used for supplying heat;

FIG. 13 is a schematic view of a rotor structure of a motor in a heating mode using an electric heater or a cogeneration mode;

FIG. 14 is a third schematic view of the rotor structure of the motor when an electric heater or a cogeneration mode is used for supplying heat;

FIG. 15 is a schematic view of a rotor of a motor with an electric heater or a cogeneration system;

FIG. 16 is a schematic view showing a rotor structure of a motor in a heating mode using an electric heater or a cogeneration mode;

fig. 17 is a sixth schematic view of a rotor structure of the motor when an electric heater or a cogeneration mode is used for supplying heat.

Detailed Description

In order to better understand the technical solution of the present invention, the present invention will be further explained with reference to the following specific embodiments and the accompanying drawings.

The utility model provides an its mainly used of miniature gas turbine of high combustion efficiency provides the heat source for heating equipment.

As shown in FIGS. 1 to 8, the embodiment of the present invention provides a micro gas turbine structure with high combustion efficiency. The system mainly comprises a compressor 20, a turbine 21 and a combustion chamber assembly. The working process comprises the following steps: the gas firstly enters the gas compressor 20, after being pressurized by the gas compressor 20, the gas enters the combustion chamber 231 of the combustion chamber assembly for combustion, and hot combustion products, namely high-temperature gas, are sprayed out from the outlet of the combustion chamber 231, so that a heat source can be provided for heating equipment; meanwhile, the high-temperature gas pushes the turbine 21 to rotate, so as to drive the compressor 20 coaxially connected with the turbine through the rotating shaft 24 to rotate, and thus, the compressor 20 does not need to be driven by other devices during operation, and the operation cost of the equipment can be effectively reduced.

Specifically, the combustion chamber assembly includes a combustion chamber 231, an intake chamber 232, an intake passage 234, and an exhaust passage 235;

the air inlet cavity 232 is arranged around the combustion chamber 231, the air inlet cavity 232 comprises an integrated annular inner air inlet cavity 2321 and an integrated annular outer air inlet cavity 2322, an air outlet end at the tail end of the outer air inlet cavity 2322 is communicated with an air inlet end of the inner air inlet cavity 2321 in a winding mode and surrounds the combustion chamber 231, the air inlet end of the air inlet cavity 232 is connected with the air inlet channel 234, and the air inlet channel 234 receives air from the compressor 20;

the combustion chamber 231 is annular and disposed between the inner intake cavity 2321 and the outer intake cavity 2322, with the inner intake cavity 2321 and the outer intake cavity 2322 being disposed radially inward and outward of the combustion chamber 231, respectively. The combustion chamber air outlet 2311 is communicated with the front part of the exhaust channel 235, the exhaust channel 235 is annular and is arranged around the axis of the rotating shaft 24 along the radial direction of the gas turbine 2, and the combustion chamber air outlet 2311 is arranged at the front part of the exhaust channel 235 and is positioned at the front side of the turbine 21;

the radially inner wall 2312 and the radially outer wall 2313 of the combustion chamber 231 are provided with air holes for allowing the air of the outer air intake cavity 2322 and the inner air intake cavity 2321 to enter the combustion chamber 231, and the radially inner wall 2312 and the radially outer wall 2313 separate the combustion chamber 231 from the inner air intake cavity 2321 and the outer air intake cavity 2322 respectively.

Preferably, support ribs 27 may be added between the walls of the combustion chamber 231, the intake chamber 232, the exhaust passage 235, and the intake passage 234 to increase the overall strength of the combustion chamber assembly.

Preferably, portions of the combustion chamber 231 are made of a high temperature resistant material, such as stainless steel.

The utility model discloses an impeller 201 and the turbine 21 coaxial coupling of compressor 20 install in pivot 24, and the turbine 21 rim stretches into in the exhaust passage 235 around its pivot 24. In this way, the hot combustion products ejected from the exhaust passage 235 can drive the turbine 21 to rotate at a high speed, and the compressor is driven to rotate by the turbine 21.

Preferably, the rim of the turbine 21 is perpendicular to the exhaust passage 235, and the turbine 21 is an axial flow turbine.

Preferably, the air inlet channel 234 of the combustion chamber assembly is arranged around the rotating shaft 24, the air inlet cavity 232 at the tail end of the air inlet channel 234, the combustion chamber 231 and the exhaust channel 235 are all arranged around the turbine 21 and extend out of the turbine 21, and the edge of the turbine 21 extends into the exhaust channel 235 and is arranged facing the exhaust; the combustion chamber 231 tapers in diameter near the outlet end.

Preferably, the compressor 20 further comprises an air inlet cylinder 202 and a rear end cover 203 which are integrated, and the impeller 201 is sleeved and fixed at the front end of the rotating shaft 24;

a front fixed end cover 25 is sleeved on the rotating shaft 24 close to the impeller 201, and a gas outlet channel 204 of the gas compressor is formed in a gap between the front fixed end cover 25 and the rear end cover 203; the air inlet channel 234 of the combustion chamber 231 comprises an inner side wall and an outer side wall, the front end of the inner side wall is fixed at the edge of the front fixed end cover 25, and the outer side wall is fixed at the edge of the rear end cover 203 of the compressor 20;

the rotating shaft 24 is sleeved with a rear fixed end cover 26 close to the turbine 21, and the wall of the combustion chamber assembly 23 close to the rear fixed end cover 26 is fixed with the combustion chamber assembly. The structure arrangement makes the structure of the compressor 20 and the combustion chamber assembly compact and small in occupied space.

Preferably, sealing elements are arranged between the rim of the turbine 21 and the exhaust channel 235, between the rotating shaft 24 and the front fixed end cover 25, between the rotating shaft 24 and the rear fixed end cover 26, and between the turbine 21 and the rear fixed end cover 26 to ensure the sealing performance.

The micro gas turbine of the present invention has a compact structure and a minimized axial length, and can ensure that the pressure of the fuel gas supplied to the combustion chamber 231 is automatically matched with the pressure of the air regardless of the rotation speed of the rotor assembly; meanwhile, the air inlet cavity 232 surrounds the combustion chamber 231 in a C shape, the annular inner air inlet cavity 2321 and the annular outer air inlet cavity 2322 are connected in a winding mode, an air inlet path is increased, and due to the fact that high temperature in the combustion chamber 231 can preheat gas of each part of the air inlet cavity 232 through heat exchange, reaction efficiency is improved; on the other hand, air can be introduced in all directions of the wall of the combustion chamber 231, so that the combustion reaction is more sufficient; the combustion chamber air outlet 2311 is arranged on the front side of the turbine 21, the axial length of the rotating shaft 24 is short, the rotor rotates more stably, and the size of the whole machine is small.

The embodiment of the present invention also provides a plurality of supporting structures for the rotating shaft 24 of the micro gas turbine. The specific structure is described in the following embodiments one to eight.

Example one

Referring to fig. 1 in the embodiment, a thrust disc is arranged in the middle of a rotating shaft 24 of a micro gas turbine 2, and a thrust bearing 241 is sleeved on the thrust disc; radial bearings 242 are respectively sleeved at two ends of the rotating shaft 24.

Thrust bearing 241: the first bearing body 2411 and the second bearing body 2412 are symmetrically arranged with the thrust disc in the axial direction and have a preset first axial gap S1; the outer end walls of the first bearing body 2411 and the second bearing body 2412 are respectively provided with a first air groove and a second air groove, the bottoms of the first air groove and the second air groove are provided with through air holes, and the air holes are communicated with the air grooves and the corresponding first axial gaps S1; a third radial gap S3 is preset between the inner rings of the first bearing body 2411 and the second bearing body 2412 and the rotating shaft 24; a fourth radial gap S4 is provided between the side wall of the thrust disc accommodating groove 244 surrounded by the first bearing body 2411 and the second bearing body 2412 and the side wall of the thrust disc.

The radial bearing 242: is arranged on the rotating shaft 24, and the outer wall of the rotating shaft is provided with an air groove; a predetermined second radial gap S2 is provided between the inner wall of the radial bearing 242 and the rotating shaft 24; the bottom of the air groove is provided with a through air hole which is communicated with the air groove and the second radial gap S2.

The inlet pipe 243 is provided in the micro gas turbine 2 to supply air to each air tank, and the air enters the first axial gap S1 and the second radial gap S2 along the inlet hole to form an air film.

Preferably, the thrust bearing 241 of the present embodiment further includes a first bearing housing 281 and a second bearing housing 282, the first bearing housing 281 includes an end portion and a circumferential portion, the end portion is mounted on the outer end of the first bearing body 2411, and the circumferential portion is sealed and covered on the outer periphery of one radial bearing 242; the second bearing housing 282 includes first and second stepped cylindrical circumferential portions, the first circumferential portion being housed in the outer peripheries of the first and

second bearing bodies

2411 and 2412, and the second circumferential portion being hermetically housed in the outer periphery of the other radial bearing 242. The first circumferential portion of the second bearing housing 282 is axially fixed to the end of the first bearing housing 281. The first bearing housing 281 and/or the second bearing housing 282 are stationary components.

The first bearing housing 281 or/and the second bearing housing 282 have relief holes.

Specifically, the thrust bearing 241 and the radial bearing 242 of the present embodiment are both air bearings, and may be any of a static pressure gas bearing, a dynamic pressure gas bearing, or a hybrid dynamic and static pressure gas bearing.

Example two

Referring to fig. 2, in the first embodiment, a thrust bearing 241 is integrally connected to a radial bearing 242 by a thrust disk end portion; the third radial gap S3 is a tapered gap and decreases toward the radial bearing 242.

EXAMPLE III

Referring to fig. 3, in the present embodiment, a thrust disc is disposed at one end of the rotating shaft 24 of the micro gas turbine 2 close to the turbine 21, and a thrust bearing 241 is sleeved on the thrust disc; a radial bearing 242 is sleeved on one end of the rotating shaft 24 close to the impeller 201 of the compressor 20.

Thrust bearing 241: the first bearing body 2411 and the second bearing body 2412 are arranged on the rotating shaft 24, are symmetrically arranged with the thrust disc in the axial direction and have a preset first axial gap S1; the outer end walls of the first bearing body 2411 and the second bearing body 2412 are respectively provided with a first air groove and a second air groove, the bottoms of the first air groove and the second air groove are provided with through air holes, and the air holes are communicated with the air grooves and the corresponding first axial gaps S1; a third radial gap S3 is preset between the inner rings of the first bearing body 2411 and the second bearing body 2412 and the rotating shaft 24; a fourth radial gap S4 is provided between the side wall of the thrust disc accommodating groove 244 surrounded by the first bearing body 2411 and the second bearing body 2412 and the side wall of the thrust disc.

Preferably, the thrust bearing 241 of the embodiment further includes a first bearing housing 281 and a second bearing housing 282, the first bearing housing 281 includes an end portion and a circumferential portion, the end portion is mounted on one end of the first bearing body 2411, the circumferential portion is hermetically covered on the outer periphery of the radial bearing 242, the second bearing housing 282 includes a circumferential portion and an end portion, the circumferential portion is covered on the outer periphery of the first bearing body 2411 and the second bearing body 2412, the end portion is mounted on the outer end of the second bearing body 2412, and the circumferential portion of the second bearing housing 282 is axially fixed with the end portion of the first bearing housing 281. The first bearing housing 281 and/or the second bearing housing 282 are stationary components.

Example four

Referring to fig. 4, in the third embodiment, a thrust bearing 241 is integrally connected to a radial bearing 242 by a thrust disk end portion; the third radial gap S3 is a tapered gap and decreases toward the radial bearing 242.

EXAMPLE five

In the embodiment, referring to fig. 5, a thrust disc is arranged at one end of the rotating shaft 24 of the micro gas turbine 2 close to the impeller 201 of the compressor 20, and a thrust bearing 241 is sleeved on the thrust disc; one end of the rotating shaft 24 close to the turbine 21 is sleeved with a radial bearing 242.

Preferably, the thrust bearing 241 of the present embodiment further includes a first bearing housing 281 and a second bearing housing 282, the first bearing housing 281 includes an end portion, the end portion of the first bearing housing 281 is mounted on one end of the first bearing body 2411, the second bearing housing 282 includes a circumferential portion and an end portion, the circumferential portion covers the outer peripheries of the first bearing body 2411 and the second bearing body 2412, the end portion of the circumferential portion is mounted on the outer end of the second bearing body 2412, and the circumferential portion of the second bearing housing 282 is axially fixed to the end portion of the first bearing housing 281. The radial bearing 242 further includes a radial bearing housing sleeved on the outer periphery thereof, the radial bearing housing is fixed to the circumferential portion of the second bearing housing 282, and the first bearing housing 281 and/or the second bearing housing 282 are stationary components.

EXAMPLE six

Referring to fig. 6, in the fifth embodiment, a thrust bearing 241 is integrally connected to a radial bearing 242 by a thrust disk end portion; the third radial gap S3 is a tapered gap and decreases toward the radial bearing 242.

EXAMPLE seven

Referring to fig. 7, the rotating shaft 24 is not provided with a thrust disc, and two ends of the rotating shaft 24 are sleeved with thrust bearings 241 and the middle part is sleeved with a radial bearing 242.

Thrust bearing 241: the impeller comprises a first bearing body 2411 and a second bearing body 2412, wherein a preset first axial clearance S1 is respectively formed between the first bearing body 2411 and the impeller 201 and between the second bearing body 2412 and the turbine 21; the end walls of the first bearing body 2411 and the second bearing body 2412 close to the radial bearing 242 are respectively provided with a first air groove and a second air groove, the bottoms of the first air groove and the second air groove are provided with through air holes, and the air holes are communicated with the air grooves and the corresponding first axial gaps S1; a third radial gap S3 is left between the inner rings of the first and

second bearing bodies

2411 and 2412 and the rotating shaft 24.

Preferably, a bearing housing is further disposed outside the bearing of the embodiment, the bearing housing is an integrated bearing housing, and includes a first bearing housing 281, a second bearing housing 282 and a radial bearing housing, the first bearing housing 281 includes an end portion, the end portion of the first bearing housing is mounted at one end of the first bearing body 2411, the second bearing housing 282 includes an end portion, the end portion of the second bearing housing is mounted at one end of the second bearing body 2412; the radial bearing shell is sleeved at the middle section of the rotating shaft 24; the bearing housing is a stationary component.

The bearing shell is provided with a pressure reducing hole.

Example eight

Referring to fig. 8, in the seventh embodiment, a thrust bearing 241 is integrally connected to an end surface portion of a radial bearing 242 by a shaft surface portion; the third radial gap S3 is a tapered gap and decreases toward the radial bearing 242.

The utility model discloses in the above-mentioned embodiment structure, through the reasonable layout to thrust bearing and journal bearing, can guarantee the steady operation of miniature gas turbine 2 under high speed.

The embodiment of the utility model provides a still be provided with the heating equipment of connecting miniature gas turbine 2, provide required energy through miniature gas turbine 2 to heating equipment, wherein heating equipment is boiler 3 or electric heater 4.

In an embodiment of the present invention, the heating equipment is a boiler 3. Referring to the structural schematic diagram of the boiler heating micro gas turbine heating equipment of fig. 9, gas firstly enters the gas compressor 20, is pressurized by the gas compressor 20 and then enters the combustion chamber 231 of the combustion chamber assembly for combustion, hot combustion products are ejected from the outlet of the combustion chamber 231, meanwhile, the high-temperature gas pushes the turbine 21 to rotate, the gas compressor 20 coaxially connected with the turbine is driven to rotate through the rotating shaft 24, and the hot combustion products ejected from the outlet of the combustion chamber 231 can provide a heat source for the boiler 3 to heat boiler water, so that the heating purpose is achieved.

In another embodiment provided by the present invention, the heating device is the motor 22 and the electric heater 4. Referring to fig. 10, a schematic diagram of a micro gas turbine heater for electric heater heating; the gas firstly enters the compressor 20, is pressurized by the compressor 20 and then enters the combustion chamber 231 of the combustion chamber assembly 23 for combustion, and hot combustion products are ejected from the outlet of the combustion chamber 231. The exhaust channel 235 is positioned at the rear side of the turbine 21, and a motor impeller of the motor 22 is also arranged, at the moment, high-temperature gas can push the turbine 21 to rotate, the compressor 20 coaxially connected with the turbine through the rotating shaft 24 is driven to rotate, the motor impeller can be pushed to rotate, power is generated, a power supply is provided for the electric heater 4, the electric heater 4 generates heat, the heating purpose is achieved, and redundant high-temperature gas is discharged from the exhaust channel 235.

In another embodiment of the present invention, the heating device is a boiler 3, a motor 22, and an electric heater 4. Referring to FIG. 11, a schematic diagram of a combined heat and power micro gas turbine heating plant; the gas firstly enters the compressor 20, is pressurized by the compressor 20 and then enters the combustion chamber 231 of the combustion chamber assembly 23 for combustion, and hot combustion products are ejected from the outlet of the combustion chamber 231. The exhaust passage 235 is positioned at the rear side of the turbine 21, and a motor impeller of the motor 22 is also arranged, at the moment, high-temperature gas can push the turbine 21 to rotate, so as to drive the compressor 20 coaxially connected with the turbine through the rotating shaft 24 to rotate, and can also push the motor impeller to rotate, so that work is done and electricity is generated, a power supply is provided for the electric heater 4, the electric heater 4 generates heat, the purpose of heating is achieved, redundant high-temperature gas is discharged to the boiler from the exhaust passage 235, a heat source is provided for the boiler 3, boiler water is heated, the purpose of heating is achieved, and the effect of electric-heat combined heating can.

According to the heat supply machine type designed by the utility model, stable operation can be realized under the heat supply experimental condition of 100 kW; actually measuring the noise of 70db in a laboratory operating room; actually measuring NOx emission of 10ppm, which is 1/5 of the emission standard of a power plant and 1/10 of the emission standard of a boiler; HC emission was found to be 0 and combustion efficiency was found to be about 99.8%. The experimental result simultaneously shows, the utility model discloses a miniature gas turbine heating equipment combustion efficiency is high, and the noise discharges up to standard, and the pollutant discharge is up to standard to be higher than other heating system's in the trade emission standard requirement far away.

The embodiment of the utility model provides a still be provided with when adopting electric heater or combined heat and power mode heat supply electric motor rotor structure.

In one embodiment provided by the present invention,

the rotor system of the motor 22 comprises a turbine shaft for mounting a motor impeller 222 and a motor shaft for mounting a motor body 221, the impeller shaft and the motor shaft are connected through a coupler, a first bearing 223 and a second bearing 224 are arranged between the motor impeller 222 and the coupler, and the motor shaft and the motor body 221 are rotatably connected through a third bearing 225 and a fourth bearing 226.

The motor impeller 222 has a longer wheel base, and the motor impeller 222 is connected with a motor shaft through a coupler, so that heat at the end of the motor impeller 222 can be isolated, larger axial thrust at the end of the motor impeller 222 can be borne, and meanwhile, the arrangement of a flue space at the end of the motor impeller 222 is convenient.

In the structure of this embodiment, a first casing and a second casing may be further provided, and the first casing and the second casing are connected by a coupling, wherein the first bearing 223, the second bearing 224, and the motor impeller 222 are disposed in the first casing, and the motor body 221, the third bearing 225, and the fourth bearing 226 are disposed in the second casing.

In a specific structure provided in this embodiment, as shown in fig. 12, the rotor system of the motor 22 includes a thrust bearing, a first radial bearing, a second radial bearing and a third radial bearing, which are sequentially disposed, the thrust bearing is disposed between the motor impeller 222 and the coupler and near the motor impeller 222, the first radial bearing is disposed between the motor impeller 222 and the coupler and near the coupler, the second radial bearing is disposed on one side of the motor body 221 near the motor impeller 222, and the third radial bearing is disposed on the other side of the motor body 221 far from the motor impeller 222.

In another specific structure provided in this embodiment, as shown in fig. 13, the rotor system of the motor 22 includes a first radial bearing, a thrust bearing, a second radial bearing and a third radial bearing, which are sequentially disposed, the first radial bearing is disposed between the motor impeller 222 and the coupler and near the motor impeller 222, the thrust bearing is disposed between the motor impeller 222 and the coupler and near the coupler, the second radial bearing is disposed on one side of the motor body 221 near the motor impeller 222, and the third radial bearing is disposed on the other side of the motor body 221 far from the motor impeller 222.

In addition, in the present embodiment, the third and fourth bearings may be further provided as thrust bearings, and the corresponding bearing types are provided, which will not be described in detail herein.

Further, the thrust bearing adopts a gas-magnetic hybrid thrust bearing or a gas thrust bearing or a magnetic bearing, the first radial bearing adopts a gas-dynamic-static hybrid radial bearing or a gas-magnetic hybrid radial bearing, and the second radial bearing and the third radial bearing can adopt a gas-dynamic-static hybrid radial bearing or a gas-magnetic hybrid radial bearing or a ball bearing.

Because the motor impeller 222 is arranged in the exhaust channel 235, a non-contact bearing is required to be arranged on the impeller shaft to effectively isolate heat in the exhaust channel 235, prevent the heat from being conducted to the motor shaft to cause damage to the motor, and improve the reliability and safety of the power generation system of the gas turbine; the impeller shaft and the motor shaft respectively transmit power and are connected through the coupler, so that the bearing capacity of each shaft can be effectively decomposed while the motor 22 is convenient to disassemble, assemble and maintain, and the deformation of the rotating shaft caused by overlong wheelbase is prevented.

Preferably, the thrust bearing and the first radial bearing may be provided as an integral bearing having both a radial support function and an axial support function.

In another specific structure provided in this embodiment, as shown in fig. 14, the rotor system of the motor 22 includes a first radial bearing, a second radial bearing, a third radial bearing and a fourth radial bearing, which are sequentially disposed, the first radial bearing is disposed between the motor impeller 222 and the coupler and near the motor impeller 222, the second radial bearing is disposed between the motor impeller 222 and the coupler and near the coupler, the third radial bearing is disposed on one side of the motor body 221 near the motor impeller 222, and the fourth radial bearing is disposed on the other side of the motor body 221 far from the motor impeller 222.

Furthermore, the first radial bearing and the second radial bearing adopt ball bearings or air bearings, the third radial bearing and the fourth radial bearing adopt gas dynamic and static pressure mixed radial bearings or gas magnetic mixed radial bearings or ball bearings, the first radial bearing and the second radial bearing adopt ball bearings which can offset axial force and play the roles of the radial bearing and a thrust bearing simultaneously,

in addition, the third and fourth bearings may be thrust bearings, and the corresponding bearing types may be provided, which will not be described in detail herein.

In another embodiment provided by the present invention, the rotor system of the motor 22 includes a motor shaft, the motor shaft is an integrated shaft, the motor shaft is provided with a motor impeller 222 and a motor body 221, a first bearing 223 and a second bearing 224 are provided between the motor impeller 222 and the motor body 221, and the motor body 221 is provided with a third bearing 225 away from the motor impeller 222.

In a specific structure provided in this embodiment, as shown in fig. 15, a rotor system of the motor 22 includes a thrust bearing, a first radial bearing, and a second radial bearing, which are sequentially disposed on a rotating shaft of the motor.

In another specific structure provided by the present embodiment, referring to fig. 16, the rotor system includes a first radial bearing, a thrust bearing, and a second radial bearing, which are sequentially disposed on the rotating shaft of the motor.

Preferably, the thrust bearing and the first radial bearing are non-contact bearings, and the second radial bearing is a non-contact bearing or a contact bearing.

Further, the thrust bearing adopts a gas-magnetic hybrid thrust bearing or a gas thrust bearing or a magnetic bearing, the first radial bearing adopts a gas-dynamic-static hybrid radial bearing or a gas-magnetic hybrid radial bearing, and the second radial bearing can adopt a gas-dynamic-static hybrid radial bearing or a gas-magnetic hybrid radial bearing or a ball bearing.

In another specific structure provided in this embodiment, referring to fig. 17, the rotor system of the motor 22 includes a first radial bearing, a second radial bearing, and a third radial bearing sequentially disposed on the rotating shaft of the motor.

Furthermore, the first radial bearing and the second radial bearing adopt ball bearings or air bearings, the third radial bearing adopts a gas dynamic and static pressure mixed radial bearing or a gas magnetic mixed radial bearing or ball bearings, the first radial bearing and the second radial bearing adopt ball bearings to offset axial force, and the radial bearings and the thrust bearing are simultaneously used.

In the rotor system of the embodiment, the rotating speed of the motor impeller 222 is low, and compared with a conventional integrated high-speed micro gas turbine, the radial load and the axial thrust of the rotating shaft are greatly reduced, and the requirement on the strength of the rotating shaft is also reduced, so that the integrated rotating shaft can be used for connecting the motor impeller 222 and the motor body 221, the number of parts is reduced, and the design reliability is improved.

The above description is only a preferred embodiment of the application and is illustrative of the principles of the technology employed. It will be understood by those skilled in the art that the scope of the present invention is not limited to the specific combination of the above-mentioned features, but also covers other embodiments formed by any combination of the above-mentioned features or their equivalents without departing from the spirit of the present invention. For example, the features described above have similar functions to (but are not limited to) those disclosed in this application.

Claims

1. A high combustion efficiency micro gas turbine, comprising: a compressor, a turbine and a combustor assembly;

2. The high combustion efficiency micro gas turbine according to claim 1, wherein the inner air intake chamber and the outer air intake chamber are both annular, and an air outlet end at the end of the outer air intake chamber is communicated with an air inlet end of the inner air intake chamber in a winding manner and surrounds the combustion chamber;

3. The high combustion efficiency micro gas turbine according to claim 2, wherein the exhaust passage is annular and disposed around the shaft axis, and the combustor exit is disposed at a front portion of the exhaust passage and at a front side of the turbine.

4. The micro gas turbine with high combustion efficiency as claimed in claim 1, wherein the supporting ribs are disposed in the combustion chamber, the air intake cavity, the exhaust passage and the air intake channel.

5. The high combustion efficiency micro gas turbine according to claim 1, wherein the turbine is an axial flow turbine, the axial flow turbine rim being perpendicular to the exhaust channel.

6. The high combustion efficiency micro gas turbine according to claim 1, wherein the air intake passage is provided around the rotating shaft, and the air intake chamber, the combustion chamber, and the exhaust passage are provided around the turbine.

7. The high combustion efficiency micro gas turbine according to claim 6, wherein the combustion chamber is tapered near the combustion chamber outlet diameter.

8. The high combustion efficiency micro gas turbine engine of claim 1, wherein the compressor further comprises an integral inlet barrel and rear end cap; the impeller is sleeved and fixed at the front end of the rotating shaft;

9. The high combustion efficiency micro gas turbine engine of claim 8, wherein the inlet channel of the combustor assembly has its inner sidewall fixed at a front fixed end cover edge at a front end and an outer sidewall fixed at a rear end cover edge;

10. The high combustion efficiency micro gas turbine according to claim 9, wherein a seal is provided between the turbine rim and the exhaust passage, between the shaft and the front stationary cover, between the shaft and the rear stationary cover, and between the turbine and the rear stationary cover.