CN214366399U

CN214366399U - Miniature gas turbine with concave thrust structure

Info

Publication number: CN214366399U
Application number: CN202022677160.3U
Authority: CN
Inventors: 靳普
Original assignee: Individual
Current assignee: Liu Muhua
Priority date: 2020-11-18
Filing date: 2020-11-18
Publication date: 2021-10-08
Anticipated expiration: 2030-11-18

Abstract

The utility model discloses a concave thrust structure micro gas turbine, which comprises a rotor system, a motor casing, a gas turbine casing and a combustion chamber, wherein the rotor system comprises a rotating shaft, a thrust bearing, a first radial bearing, a motor, a gas compressor, a second radial bearing and a turbine are sequentially arranged on the rotating shaft, and a third bearing is arranged between the rotating shaft and a side coil of the motor close to the gas compressor; the motor casing is covered on the periphery of the motor; the gas turbine casing is covered on the peripheries of the gas compressor and the turbine and is connected with the motor casing; the combustion chamber is connected with the gas turbine casing; thrust discs are arranged on two sides of the thrust bearing and fixedly connected with the rotating shaft. The utility model discloses a miniature gas turbine of concave thrust structure, the bearing at both ends is passed through in the pivot supports, can avoid because of the unbalanced weight that rotor shaft end suspension leads to, and the operation stationarity is good. Two thrust discs are small, the consumptive material is few, the technology is simple relatively than single thrust disc processing turning volume, mass distribution is even relatively, and stability is better when the high rotation of pivot.

Description

Miniature gas turbine with concave thrust structure

Technical Field

The utility model relates to a miniature gas turbine of concave thrust structure belongs to miniature gas turbine technical field.

Background

In the field of micro gas turbine power generation, a micro gas turbine power generator set generally includes a coaxially mounted generator and a micro gas turbine. Specifically, the micro gas turbine mainly comprises three parts, namely a gas compressor, a combustion chamber and a turbine, wherein air is compressed into high-temperature and high-pressure air after entering the gas compressor, then the high-temperature and high-pressure air is supplied to the combustion chamber to be mixed and combusted with fuel, and the generated high-temperature and high-pressure gas expands in the turbine to do work to push the turbine to rotate so as to drive the generator to generate electricity. Because the magnetic components and coil windings in the generator are not high-temperature resistant, the generator cannot be arranged at the hot end of the rotor system, namely one side of the turbine; in the prior art, a generator is generally installed at an air inlet end of a rotating shaft of a micro gas turbine, namely an air inlet end of a compressor. In order to support the rotating shaft, radial bearings are arranged between the rotating shaft and the stator and positioned at two end parts of the stator to be used as fulcrums; the tail part (namely the gas outlet end) of the gas turbine is also provided with components such as a gas compressor, a turbine, a combustion chamber and the like, so that the weight is large, and the following problems exist: the rotating shaft cannot be too long, otherwise, the problems of downward inclination of the tail part, upwarp of the head part, unstable operation of the rotor, serious vibration and the like can be caused.

In addition, the epaxial thrust dish that currently commonly uses is mostly protruding formula, and its problem that exists is, and thrust dish and pivot an organic whole are made, add man-hour, need on whole root axle material turning process, because the thrust dish height is great, can produce great turning volume, extravagant material, and because the turning number of times is many, need destressing many times, the technology is complicated. Moreover, because a single thrust disc is heavy in weight, when the rotating shaft rotates at a high speed, inertia force can be generated, the rotating shaft is caused to deviate from the axis to rotate, and the rotating stability is poor and the vibration is serious in a rotor system.

Disclosure of Invention

To the above-mentioned prior art, the utility model provides a miniature gas turbine of concave thrust structure. The utility model discloses a miniature gas turbine of concave thrust structure arranges the pivot both ends in with two branches branch, makes the pivot equilibrium better, and rotor system operating stability is good. The utility model discloses can solve pivot afterbody size restriction, solve rotor system and move unstability, shake serious problem to can solve current integral type thrust bearing structure complicacy, easily destroyed technical problem.

The utility model discloses a realize through following technical scheme:

a concave thrust structure micro gas turbine comprises a rotor system, a motor casing, a gas turbine casing and a combustion chamber, wherein the rotor system comprises a rotating shaft, a thrust bearing, a first radial bearing, a motor, a gas compressor, a second radial bearing and a turbine are sequentially arranged on the rotating shaft, and a third bearing (namely a rotating shaft outer sleeve bearing and a bearing outer sleeve coil) is arranged between the rotating shaft and a side coil of the motor close to the gas compressor; the motor casing is covered on the periphery of the motor; the gas turbine casing is covered on the peripheries of the gas compressor and the turbine and is connected with the motor casing; the combustion chamber is connected with the gas turbine casing, the gas inlet of the combustion chamber is connected with the gas outlet of the gas compressor, and the gas outlet of the combustion chamber is connected with the gas inlet of the turbine; thrust discs are arranged on two sides of the thrust bearing and fixedly connected with the rotating shaft; the two thrust discs and the thrust bearing are concave to form a concave thrust structure.

Further, the structure of the thrust bearing is as follows: the left bearing unit and the right bearing unit are arranged oppositely, an air cavity is arranged between the two bearing units, an air inlet on the bearing shell continuously ventilates, the air enters the bearing air cavity along a gap between the two bearing units, air holes of the two bearing units enter the two sides, an air film is formed between the bearing units and the thrust disc, and the axial thrust effect is achieved.

Further, the third bearing is made of one or more of nylon reinforced plastics, polyethylene, polycarbonate, carbon fiber, glass fiber, aluminum oxide and silicon carbide.

Furthermore, a diffuser is arranged between the exhaust port of the compressor and the air inlet of the combustion chamber so as to further improve the pressure of the high-temperature and high-pressure gas entering the turbine for doing work.

Furthermore, a reinforcing ring is arranged between the gas compressor and the turbine, the second radial bearing is sleeved on the reinforcing ring, and the reinforcing ring is supported in the second radial bearing by means of a gas film. The function of setting up the beaded finish is: the requirement on the rigidity of the rotor (the high requirement on the strength of the rotating shaft in the high-speed rotating process of the rotor system) is met, and meanwhile, the reinforcing ring can be used as a mounting shaft of the second radial bearing.

Furthermore, the rotating shaft comprises a first shaft section and a second shaft section which are integrally formed, the diameter of the first shaft section is larger than that of the second shaft section, and a step surface is formed at the transition position of the first shaft section and the second shaft section.

Further, the thrust bearing, the first radial bearing and the motor are arranged on the first shaft section; the compressor, the second radial bearing and the turbine are arranged on the second shaft section; one end of the compressor is abutted against the step surface.

Further, the shaft diameter of the second shaft section can be made thin (for rotor dynamic performance reasons, the lighter the weight of the shaft, the lighter the diameter of the shaft).

Further, the first radial bearing, the second radial bearing or/and the third bearing is/are air bearings. The air bearing may be a dynamic pressure air bearing, a static pressure air bearing or a hybrid dynamic and static pressure air bearing.

The utility model discloses a miniature gas turbine of concave thrust structure, the bearing that both ends were passed through in the pivot supports (first journal bearing and second journal bearing promptly), and the atress is even, can avoid because of the unbalanced by weight that rotor shaft end suspension leads to, and the operation stationarity is good, and the axial direction of pivot goes up the size adjustable range great. Two thrust discs are small, the consumptive material is few, the technology is simple relatively than single thrust disc processing turning volume, mass distribution is even relatively, and stability is better when the high rotation of pivot.

The utility model discloses a miniature gas turbine of concave thrust structure, all bearings are all set up in motor cartridge receiver, only need guarantee in this cartridge receiver like this be used for setting up the machining precision at the position of bearing stator can, the position that is used for connecting the bearing stator in this cartridge receiver when the assembly can be accomplished through the processing of once adorning the card, and is visible, the utility model discloses reduce gas turbine generating set's machining precision and assembly precision, the cost is reduced is fit for engineering batch production.

The various terms and phrases used herein have the ordinary meaning as is well known to those skilled in the art. To the extent that the terms and phrases are not inconsistent with a known meaning, the meaning of the present invention is expressed, the specification is set forth.

Drawings

FIG. 1: is the structure schematic diagram of the concave thrust structure micro gas turbine of the utility model.

Fig. 2 is a partially enlarged view of a position a in fig. 1.

Fig. 3 is a partially enlarged view of a portion B in fig. 1.

The engine comprises a rotating shaft 100, a first shaft section 110, a first shaft section 120, a second shaft section 130, a step surface 200, a thrust bearing 300, a motor 400, a second radial bearing 500, a compressor 600, a turbine 700, a reinforcing ring 810, a motor casing 820, a gas turbine casing 830, a combustion chamber 840, a diffuser 900, a first radial bearing and a third bearing 910.

Detailed Description

The present invention will be further described with reference to the following examples. However, the scope of the present invention is not limited to the following examples. Those skilled in the art will appreciate that various changes and modifications may be made to the invention without departing from the spirit and scope of the invention.

EXAMPLE 1 Recessed thrust Structure micro gas turbine

A micro gas turbine with a concave thrust structure comprises a rotor system, a motor casing 810, a gas turbine casing 820 and a combustion chamber 830, as shown in FIGS. 1, 2 and 3.

The rotor system comprises a rotating shaft 100, wherein the rotating shaft 100 comprises a first shaft section 110 and a second shaft section 120 which are integrally formed, the diameter of the first shaft section 110 is larger than that of the second shaft section 120, and a step surface 130 is formed at the transition position of the first shaft section 110 and the second shaft section 120; the first shaft segment 110 is sequentially provided with a thrust bearing 200, a first radial bearing 900 and a motor 300; the second shaft section 120 is sequentially provided with a compressor 500, a second radial bearing 400 and a turbine 600; one end of the compressor 500 abuts against the step surface 130; a third bearing 910 is arranged between the rotating shaft 100 and a coil of the motor 300 close to the compressor, coils are arranged on the left side and the right side of the motor 200 in fig. 1, and the coil of the close compressor is a right coil of the motor 200 (the position of the third bearing 910 is below the right coil of the motor 300).

The motor housing 810 covers the outer circumference of the motor 300. The gas turbine casing 820 covers the outer peripheries of the compressor 500 and the turbine 600, and is connected to the motor casing 810. The combustion chamber 830 is connected to the gas turbine case 820, and an intake port of the combustion chamber 830 is connected to an exhaust port of the compressor 500, and an exhaust port of the combustion chamber 830 is connected to an intake port of the turbine 600.

Thrust discs are arranged on both sides of the thrust bearing 200 and fixedly connected with the rotating shaft 100; the two thrust discs plus thrust bearing 200 are concave in shape, forming a concave thrust structure.

The thrust bearing 200 has the following structure: the left bearing unit and the right bearing unit are arranged oppositely, an air cavity is arranged between the two bearing units, an air inlet on the bearing shell continuously ventilates, the air enters the bearing air cavity along a gap between the two bearing units, the air enters the two sides from the air holes of the two bearing units, an air film is formed between the bearing units and the thrust disc, and the axial thrust effect is achieved, as shown in figure 2.

The third bearing 910 is made of one or more of nylon reinforced plastic, polyethylene, polycarbonate, carbon fiber, glass fiber, alumina, and silicon carbide.

A diffuser 840 is disposed between an exhaust port of the compressor 500 and an intake port of the combustion chamber 830 to further increase the pressure of the high-temperature and high-pressure gas entering the turbine 600 to perform work.

In order to consider both the rotor dynamics and the strength of the rotating shaft (in terms of rotor dynamics, the weight of the rotating shaft is better if the weight is lighter, and the weight is lighter if the diameter of the rotating shaft is smaller; however, during high-speed rotation of the rotor system, the strength of the rotating shaft is high), the shaft diameter of the second shaft section 120 may be set to be thin, and a reinforcing ring 700 is fixedly installed between the compressor 500 and the turbine 600 to meet the requirement of the rotor rigidity, and the reinforcing ring 700 may be used as an installation shaft of the second radial bearing 400.

The first radial bearing 900, the second radial bearing 400 and the third bearing are air bearings, and the air bearings may be dynamic pressure air bearings, static pressure air bearings or dynamic and static pressure mixed air bearings.

Above-mentioned miniature gas turbine of concave thrust structure, the pivot passes through the bearing support at both ends (be first radial bearing and second radial bearing), and the atress is even, can avoid the weight unbalance because of rotor shaft end suspension leads to, and the operation stationarity is good, and the size adjustable range is great in the axial direction of pivot. Two thrust discs are small, the consumptive material is few, the technology is simple relatively than single thrust disc processing turning volume, mass distribution is even relatively, and stability is better when the high rotation of pivot.

Above-mentioned miniature gas turbine of concave thrust structure, all bearings are all set up in motor machine casket, only need guarantee in this machine casket like this be used for setting up the machining precision of the position of bearing stator can, the position that is used for connecting the bearing stator in this machine casket can be accomplished through the processing of once installing the card when the assembly, has reduced gas turbine generating set's machining precision and assembly precision, and the cost is reduced is fit for engineering batch production.

The above examples are provided to those of ordinary skill in the art to fully disclose and describe how to make and use the claimed embodiments, and are not intended to limit the scope of the disclosure herein. Modifications apparent to those skilled in the art are intended to be within the scope of the appended claims.

Claims

1. The utility model provides a miniature gas turbine of concave thrust structure which characterized in that: the gas turbine engine comprises a rotor system, a motor casing, a gas turbine casing and a combustion chamber, wherein the rotor system comprises a rotating shaft, a thrust bearing, a first radial bearing, a motor, a gas compressor, a second radial bearing and a turbine are sequentially arranged on the rotating shaft, and a third bearing is arranged between the rotating shaft and a side coil of the motor close to the gas compressor; the motor casing is covered on the periphery of the motor; the gas turbine casing is covered on the peripheries of the gas compressor and the turbine and is connected with the motor casing; the combustion chamber is connected with the gas turbine casing, the gas inlet of the combustion chamber is connected with the gas outlet of the gas compressor, and the gas outlet of the combustion chamber is connected with the gas inlet of the turbine; thrust discs are arranged on two sides of the thrust bearing and fixedly connected with the rotating shaft.

2. The concave thrust geometry micro gas turbine as set forth in claim 1, wherein: the structure of the thrust bearing is as follows: the left bearing unit and the right bearing unit are arranged oppositely, and an air cavity is arranged between the two bearing units.

3. The concave thrust geometry micro gas turbine as set forth in claim 1, wherein: a diffuser is arranged between the exhaust port of the compressor and the air inlet of the combustion chamber.

4. The concave thrust geometry micro gas turbine as set forth in claim 1, wherein: a reinforcing ring is arranged between the gas compressor and the turbine, the second radial bearing is sleeved on the reinforcing ring, and the reinforcing ring is supported in the second radial bearing by means of a gas film.

5. The concave thrust geometry micro gas turbine as set forth in claim 1, wherein: the rotating shaft comprises a first shaft section and a second shaft section which are integrally formed, the diameter of the first shaft section is larger than that of the second shaft section, and a step surface is formed at the transition position of the first shaft section and the second shaft section.

6. The concave thrust geometry micro gas turbine as set forth in claim 5, wherein: the thrust bearing, the first radial bearing and the motor are arranged on the first shaft section; the compressor, the second radial bearing and the turbine are arranged on the second shaft section; one end of the compressor is abutted against the step surface.

7. The concave thrust geometry micro gas turbine as set forth in claim 1, wherein: the first radial bearing, the second radial bearing and the third bearing are air bearings.

8. The concave thrust geometry micro gas turbine engine of claim 7, wherein: the air bearing is a dynamic pressure air bearing, a static pressure air bearing or a dynamic and static pressure mixed air bearing.