CN214577379U - Miniature gas turbine with single-tube detonation combustion chamber - Google Patents

Abstract

The utility model discloses a micro gas turbine with a single-tube detonation combustor, which comprises a gas compressor, a turbine and a combustor, wherein the gas compressor and the turbine are respectively sleeved at two ends of a rotating shaft, and the combustor is arranged at the peripheries of the gas compressor, a stator and the turbine; the combustion chamber is a single-tube detonation combustion chamber, an air outlet of the air compressor is communicated with an inlet of a detonation tube, an outlet of the detonation tube converges, and exhaust gas of the detonation tube is directly injected to the end face of the turbine to push the turbine to rotate; a fuel nozzle and an igniter are also arranged in the detonation tube; the cross section of the detonation tube is annular and wraps the rotating shaft of the gas turbine in a surrounding mode, and the detonation tube is fixed with the stator of the gas turbine. The micro gas turbine of the utility model has simple structure of the combustion chamber and does not need a complex flame stabilizer; compressed air in the combustion chamber can completely participate in combustion; the flame of the combustion chamber is transmitted at supersonic speed, the problems of combustion stability and flameout do not exist, the combustion chamber does not need to be subjected to a combustion adjustment test, and meanwhile, the emission of combustion pollutants is low.

Description

Miniature gas turbine with single-tube detonation combustion chamber

Technical Field

The scheme relates to the technical field of micro gas turbines, in particular to a micro gas turbine with a single-tube detonation combustor.

Background

The isobaric combustion is a slow combustion, the flame propagation speed of which is low, generally about several meters to ten and several meters per second, and the gas turbine has a high outlet flow rate of a compressor, so that the flame of a combustion chamber is easily blown out.

The gas turbine based on the isobaric combustion mainly has the following problems: 1. the combustion chamber has a complex structure; 2. the cooling system of the combustion chamber is complex, a large amount of air is needed for cooling the combustion chamber, and the proportion of air actually participating in combustion is small; 3. the combustion stability area of the combustion chamber is narrow, the flameout is easy, and the flame of the combustion chamber needs to be stabilized by a complex flame stabilization structure; 4. The combustion chamber control system is complex; 5. frequent combustion adjustment tests are required; 6. the improvement of the overall performance of the gas turbine thermodynamic cycle is limited by the high temperature resistant materials of the turbine.

The pulse detonation engine is a new concept engine which utilizes pulse detonation combustion waves to generate thrust. Because the propagation speed of the detonation wave is extremely fast (reaching several kilometers per second), so that the combustion products cannot expand in time in the combustion process, the detonation process is very close to the constant volume combustion process and belongs to detonation combustion, and therefore, theoretically, the cycle thermal efficiency of the detonation wave is obviously higher than that of a conventional aircraft engine based on constant pressure combustion.

Disclosure of Invention

The utility model provides a miniature gas turbine with single tube detonation combustion chamber replaces miniature gas turbine's traditional isobaric combustion mode with the constant volume combustion mode of detonation to solve above-mentioned problem.

In order to achieve the purpose, the utility model adopts the following scheme:

a micro gas turbine with a single-pipe detonation combustion chamber comprises a gas compressor, a turbine and a combustion chamber, wherein the gas compressor and the turbine are respectively sleeved at two ends of a rotating shaft, and the combustion chamber is arranged at the peripheries of the gas compressor, a stator and the turbine. The compressor and the turbine rotate along with the rotating shaft. The rotating shaft is supported in the stator through an air bearing, and the air bearing supplies air through an air pump.

An air outlet of the air compressor is communicated with an inlet of the detonation pipe, an outlet of the detonation pipe converges, and exhaust of the detonation pipe is directly injected to the end face of the turbine to push the turbine to rotate; a fuel nozzle and an igniter are also arranged in the detonation tube; the cross section of the detonation tube is annular and wraps the rotating shaft of the gas turbine in a surrounding mode, and the detonation tube is fixed with the stator of the gas turbine.

Furthermore, the gas outlet of the detonation tube is communicated with the gas flues, the side wall of each gas flue, which is close to the rotating shaft, is provided with an opening, the rim of the turbine extends into the opening of the gas flue for rotation, and the gas exhausted by the detonation tube pushes the turbine to rotate and then is discharged from the gas flues, so that the gas can be further recycled.

The utility model discloses a gas turbine working process does: and starting the gas compressor, wherein gas flows out from the gas compressor after passing through the detonation tube to push the turbine to rotate, the coaxial gas compressor is further driven to rotate, the explosive mixed gas is sprayed into the detonation tube through the fuel nozzle after the rotor system reaches the working rotating speed, the igniter is started to ignite and trigger the explosive mixed gas in the detonation tube to start detonation, and the other end of the detonation tube exhausts gas to push the turbine to rotate to continuously do work. And the gas after pushing the turbine to do work is discharged as waste heat.

Furthermore, the gas turbine further comprises a starting integrated motor, the starting integrated motor is sleeved on the rotating shaft and located on the outer side of the gas compressor, the starting integrated motor is used as a motor to drive the gas compressor to start initially, and after the rotor system is accelerated to be capable of running independently, the turbine rotates to drive the coaxial gas compressor and the starting integrated motor used as a generator to generate electricity. And the gas after pushing the turbine to do work is discharged as waste heat.

Furthermore, the gas turbine also comprises a free turbine, a free rotating shaft and a generator, wherein the free turbine is sleeved on the free rotating shaft and is arranged at the rear side of the turbine, the axis of the free turbine is collinear with the rotating shaft, and the exhaust end of the turbine is connected to the air inlet of the free turbine blade edge; the tail end of the free turbine is sleeved with a generator to generate electricity. When the gas turbine works, working medium enters from the inlet of the gas compressor, is compressed by the gas compressor and then enters the combustion chamber from the outlet of the gas compressor, high-temperature high-pressure gas ejected after ignition and combustion in the combustion chamber pushes the turbine to do work, the turbine drives the coaxial gas compressor to work, the high-temperature high-pressure gas after doing work is discharged, and the free turbine on the rear side of the turbine is pushed to rotate so as to drive the generator coaxial with the turbine to generate power. And pushing the gas after the free turbine does work to be discharged as waste heat.

Still further, the gas turbine includes a regenerator to improve combustion efficiency. The heat regenerator comprises a first inlet, a first outlet, a second inlet and a second outlet; the working medium enters the first inlet of the heat regenerator from the inlet of the compressor, is compressed by the compressor, then enters the first inlet of the heat regenerator from the outlet of the compressor, flows out of the first outlet, enters the combustion chamber for combustion, then enters the inlet of the turbine, works by the turbine, enters the second inlet of the heat regenerator from the outlet of the turbine, exchanges heat in the heat regenerator, and then flows out of the second outlet of the heat regenerator.

The waste heat discharged by the gas turbine still has higher temperature, and the waste heat can be recycled by using a waste heat recovery system.

The waste heat recovery system comprises a heat exchange unit, a circulating water tank, a pump and a power generation device, wherein a waste heat exhaust port of the gas turbine is connected with an air inlet of the heat exchange unit and used for providing a heat source for the heat exchange unit;

an air outlet of the heat exchange unit is communicated with the atmosphere, a water inlet of the heat exchange unit is connected with a water outlet of the circulating water tank, and a steam outlet of the heat exchange unit is connected with the pump and used for enabling high-pressure steam to enter the pump to do work;

the pump is connected with the power generation device and is used for driving the power generation device to generate power;

the circulating water tank is connected with a pump and used for recovering water or water-vapor mixture converted from water vapor after work is done.

Further, the pump is one of a piston pump or a roots pump or a screw pump.

Compared with the prior art, the utility model the advantage lie in: the combustion chamber has simple structure and does not need a complex flame stabilizer; compressed air in the combustion chamber can completely participate in combustion; the flame of the combustion chamber is transmitted at supersonic speed, the problems of combustion stability and flameout do not exist, the combustion chamber does not need to be subjected to a combustion adjustment test, and meanwhile, the emission of combustion pollutants is low; in addition, the combustion process has the self-pressurization characteristic, the pressure drop ratio is greater than the pressure inlet ratio, and the exhaust temperature is lower, so the stage number of the compressor can be reduced, the power consumption of the compressor is reduced, the power generation capacity is increased, and the cycle heat efficiency is improved.

Drawings

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

FIG. 2 is a schematic view of the structure of FIG. 1;

FIGS. 3-5 are schematic illustrations of three other embodiments of the gas turbine engine of the present invention;

FIG. 6 is a cross-sectional view taken at the location A-A of FIG. 1;

FIG. 7 is a schematic view of the waste heat recovery system of the present invention;

reference numerals: 101-a heat regenerator, 102-a compressor, 103-a starting integrated motor, 104-a turbine, 105-a combustion chamber, 1051-a detonation tube, 1052-a fuel nozzle, 1053-an igniter, 1054-a flue gas channel, 106-a rotating shaft, 301-a free turbine and 302-a generator; 200-heat exchange unit, 300-circulating water tank, 400-pump, 500-power generation device

Detailed Description

Example 1

Referring to fig. 1, the gas turbine includes a compressor 102, a turbine 104, and a combustion chamber 105, the compressor 102 and the turbine 104 are respectively sleeved on two ends of a rotating shaft 106, and the combustion chamber 105 is arranged at the periphery of the compressor 102, the stator, and the turbine 104. The compressor 102 and turbine 104 both rotate with the shaft 106. The shaft 106 is supported within the stator by an air bearing which is supplied with air by an air pump. FIG. 2 is a schematic view of the gas turbine engine shown in FIG. 1.

The combustion chamber 105 is a single-tube detonation combustion chamber, referring to fig. 1 and 6, an air outlet of the compressor 102 is communicated with an inlet of a detonation tube 1051, an outlet of the detonation tube 1051 converges, and exhaust gas of the detonation tube 1051 is directly injected to an end face of the turbine 104 to push the turbine 104 to rotate; a fuel nozzle 1052 and an igniter 1053 are also arranged in the detonation pipe 1051; the cross section of the detonation tube 1051 is annular (see fig. 6), and the detonation tube 1051 is arranged around the rotating shaft 106 of the gas turbine, and is fixed with the gas turbine stator.

The gas outlet of the detonation pipe 1051 is communicated with the flue gas channels 1054, the side wall of each flue gas channel 1054 close to the rotating shaft 106 is provided with an opening, the rim of the turbine 104 extends into the opening of the flue gas channel 1054 to rotate, and the exhaust gas of the detonation pipe 1051 pushes the turbine 104 to rotate and then is discharged from the flue gas channels 1054, so that the exhaust gas can be further recycled.

The utility model discloses a gas turbine working process does: the gas compressor 102 is started, gas flows out from the gas compressor 102 through the detonation tube 1051 to push the turbine 104 to rotate, the coaxial gas compressor 102 is further driven to rotate, after the rotor system reaches the working rotating speed, the combustible mixed gas is injected into the detonation tube 1051 through the fuel nozzle 1052, the igniter 1053 is started to ignite and trigger the combustible mixed gas in the detonation tube 18, detonation is started, and the other end of the detonation tube 1051 exhausts gas to push the turbine 104 to rotate and continuously do work. The gas after pushing the turbine 104 to do work is discharged as waste heat.

Example 2

Referring to fig. 3, based on embodiment 1, the gas turbine further includes a starting integrated motor 103, the starting integrated motor 103 is sleeved on the rotating shaft 106 and located outside the compressor 102, the starting integrated motor 103 is initially used as a motor to drive the compressor 102 to start, and after the rotor system is accelerated to be capable of operating independently, the turbine 104 rotates to drive the coaxial compressor 102 and the starting integrated motor 103 as a generator to generate electricity. The gas after pushing the turbine 104 to do work is discharged as waste heat.

Example 3

Referring to fig. 4, on the basis of embodiment 1, the gas turbine further includes a free turbine 301, a free rotating shaft and a generator 302, the free turbine 301 is sleeved on the free rotating shaft, is arranged at the rear side of the turbine 104, and has an axis collinear with the rotating shaft 106, and the exhaust end of the turbine 104 is connected to the air inlet of the blade edge of the free turbine 301; the generator 302 is sleeved at the tail end of the free turbine 301 to generate electricity. When the gas turbine works, working medium enters from the inlet of the compressor 102, is compressed by the compressor 102 and then enters the combustion chamber 105 from the outlet of the compressor, high-temperature high-pressure gas ejected after ignition and combustion in the combustion chamber 105 pushes the turbine 104 to do work, the turbine 104 drives the coaxial compressor 102 to work, the high-temperature high-pressure gas doing work on the turbine 104 is discharged, and the free turbine 301 on the rear side of the turbine is pushed to rotate so as to drive the generator 302 coaxial with the turbine to generate power. The gas which pushes the free turbine 301 to do work is discharged as waste heat.

Example 4

Referring to fig. 5, based on embodiment 1, the gas turbine includes a regenerator 101 to improve combustion efficiency. The regenerator 101 comprises a first inlet, a first outlet, a second inlet and a second outlet; the working medium enters the first inlet of the heat regenerator 101 from the inlet of the compressor 102, is compressed by the compressor 102, enters the first inlet of the heat regenerator 101 from the outlet thereof, flows out from the first outlet, enters the combustion chamber 105, is combusted, enters the inlet of the turbine 104, is worked by the turbine 104, enters the second inlet of the heat regenerator 101 from the outlet of the turbine 104, exchanges heat in the heat regenerator 101, and flows out from the second outlet thereof.

The waste heat discharged by the gas turbine still has higher temperature, and the waste heat can be recycled by using a waste heat recovery system.

Specifically, referring to fig. 7, the waste heat recovery system includes a heat exchange unit 200, a circulation water tank 300, a pump 400, and a power generation device 500, and a gas turbine waste heat exhaust port is connected to an air inlet of the heat exchange unit 200 for providing a heat source for the heat exchange unit 200;

an exhaust port of the heat exchange unit 200 is communicated with the atmosphere, a water inlet of the heat exchange unit 200 is connected with a water outlet of the circulating water tank 300, and a steam outlet of the heat exchange unit 200 is connected with the pump 400 to enable high-pressure steam to enter the pump 400 for doing work;

the pump 400 is connected with the power generation device 500 and is used for driving the power generation device 500 to generate power;

the circulation water tank 300 is connected with a pump 400 for recovering water or a water-vapor mixture converted from water vapor after work is done.

The pump 400 is one of a piston pump, a roots pump, or a screw pump.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", and the like, indicate the orientation or positional relationship indicated based on the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be construed as limiting the present invention. Furthermore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.

In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In the description of the present invention, reference to the description of the terms "one embodiment," "some embodiments," "an illustrative embodiment," "an example," "a specific example," or "some examples" or the like means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.

Claims (10)

1. A micro gas turbine with a single-pipe detonation combustion chamber is characterized in that the gas turbine comprises a gas compressor, a turbine and a combustion chamber, wherein the gas compressor and the turbine are respectively sleeved at two ends of a rotating shaft, and the combustion chamber is arranged at the peripheries of the gas compressor, a stator and the turbine; the compressor and the turbine rotate along with the rotating shaft; the rotating shaft is supported in the stator through an air bearing, and the air bearing supplies air through an air pump;

the combustion chamber is a single-tube detonation combustion chamber, an air outlet of the air compressor is communicated with an inlet of a detonation tube, an outlet of the detonation tube converges, and exhaust gas of the detonation tube is directly injected to the end face of the turbine to push the turbine to rotate; a fuel nozzle and an igniter are also arranged in the detonation tube; the cross section of the detonation tube is annular and wraps the rotating shaft of the gas turbine in a surrounding mode, and the detonation tube is fixed with the stator of the gas turbine.

2. The micro gas turbine with the single-tube detonation combustor according to claim 1, wherein an air outlet of the detonation tube is communicated with gas flues, openings are formed in side walls, close to a rotating shaft, of the gas flues, a rim of the turbine extends into the openings of the gas flues to rotate, and exhaust gas of the detonation tube pushes the turbine to rotate and then is discharged from the gas flues, so that the exhaust gas can be further recycled.

3. The micro gas turbine with the single-tube knocking combustor as claimed in claim 1, wherein the gas turbine further comprises an integrated starting motor, the integrated starting motor is sleeved on the rotating shaft and located outside the compressor, the integrated starting motor is initially used as a motor to drive the compressor to start, after the rotor system accelerates to the independent operation, the turbine rotates to drive the coaxial compressor and the integrated starting motor used as a generator to generate electricity, and gas after the turbine does work is pushed to be discharged as waste heat.

4. The micro gas turbine with the single-pipe knocking combustor according to claim 1, further comprising a free turbine, a free rotating shaft and a generator, wherein the free turbine is sleeved on the free rotating shaft and arranged at the rear side of the turbine, the axis of the free turbine is collinear with the rotating shaft, and the exhaust end of the turbine is connected to the inlet of the blade edge of the free turbine; the tail end of the free turbine is sleeved with a generator to generate electricity; when the gas turbine works, working media enter from an inlet of the gas compressor, are compressed by the gas compressor and then enter the combustion chamber from an outlet of the gas compressor, high-temperature and high-pressure gas ejected after ignition and combustion in the combustion chamber pushes the turbine to do work, the turbine drives the coaxial gas compressor to work, the high-temperature and high-pressure gas after the turbine does work is discharged, the free turbine on the rear side of the turbine is pushed to rotate so as to drive the generator coaxial with the turbine to generate power, and the gas after the free turbine does work is pushed to be discharged as waste heat.

5. The micro gas turbine with a single tube detonation combustor of claim 1, wherein the gas turbine includes a regenerator, the regenerator including a first inlet, a first outlet, a second inlet, a second outlet; the working medium enters the first inlet of the heat regenerator from the inlet of the compressor, is compressed by the compressor, then enters the first inlet of the heat regenerator from the outlet of the compressor, flows out of the first outlet, enters the combustion chamber for combustion, then enters the inlet of the turbine, works by the turbine, enters the second inlet of the heat regenerator from the outlet of the turbine, exchanges heat in the heat regenerator, and then flows out of the second outlet of the heat regenerator.

6. The micro gas turbine with the single-tube knocking combustion chamber as claimed in claim 1, further comprising a waste heat recovery system, wherein the waste heat recovery system comprises a heat exchange unit, a circulation water tank, a pump and a power generation device, and a waste heat exhaust port of the gas turbine is connected with an air inlet of the heat exchange unit for providing a heat source for the heat exchange unit.

7. The micro gas turbine with the single-tube detonation combustor as claimed in claim 6, wherein an exhaust port of the heat exchange unit is open to the atmosphere, a water inlet of the heat exchange unit is connected with a water outlet of the circulation water tank, and a vapor outlet of the heat exchange unit is connected with a pump for allowing high-pressure vapor to enter the pump to do work.

8. The micro gas turbine with the single-tube detonation combustor of claim 6, wherein the pump is coupled to a power generation device for powering the power generation device to generate electricity.

9. The micro gas turbine with the single-tube detonation combustor of claim 6, wherein the circulating water tank is connected to a pump for recovering water or a mixture of water and steam converted from steam after performing work.

10. The micro gas turbine engine with a single tube detonation combustor of claim 6, wherein said pump is one of a piston pump or a roots-type pump or a screw-type pump.

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