CN104033248B - Ground gas turbine utilizing pulse detonation combustion - Google Patents

Abstract

The invention discloses a ground gas turbine utilizing pulse detonation combustion, comprising a compressor, a gas storage chamber, multiple gas supply pipelines, multiple pulse detonation combustion chambers, a pressure shaping chamber, a turbine, a rotor and a tail nozzle. Among them, the compressor is set at the front end of the ground gas turbine, and the gas outlet of the compressor is connected with the gas storage chamber, the pressure shaping chamber, the turbine and the tail nozzle in turn, and the rotor is set at the center of the compressor and the turbine, and passes through two The bearings are respectively connected with the compressor and the turbine, and one end of the rotor is led out from the tail nozzle; multiple pulse detonation combustion chambers are arranged in the circumferential direction of the gas storage chamber and the pressure shaping chamber, and the outlets of the gas storage chambers are respectively passed through multiple supply The gas pipeline is connected with the inlets of multiple pulse detonation combustion chambers, and the outlets of multiple pulse detonation combustion chambers are respectively connected with the inlets of the pressure shaping chambers, and spark plugs and fuel pipelines are arranged on the circumference of a single pulse detonation combustion chamber. When in use, the lead-out end of the rotor is connected with the generator assembly through the transmission.

Description

A Ground Gas Turbine Using Pulse Detonation Combustion

【Technical field】

The invention relates to a gas turbine, in particular to a ground gas turbine utilizing pulse detonation combustion.

【Background technique】

All ground gas turbines use isobaric combustion to release fuel heat. Isobaric combustion is a kind of slow-burning combustion, and its flame propagation speed is relatively low, generally about a few meters to more than ten meters per second. The combustion chamber flame is easily blown out. In order to ensure the stability and reliability of the flame in the combustion chamber, it is generally necessary to carefully design the structure of the combustion chamber, using flame stabilizers such as swirlers, concave cavities, and sand dune vortexes to form a low-speed vortex area at the head of the combustion chamber, so that part of the burned high-temperature combustion products Generate backflow movement to form a continuous ignition source with automatic compensation ability to continuously ignite fresh unburned combustible mixture, so as to achieve the purpose of stabilizing the flame. However, as the market's regulations and requirements for pollutant emission indicators of ground gas turbines become increasingly strict, the design cost and technical difficulty of gas turbine combustors continue to increase. Advanced low-pollution combustors currently use lean-burn premixed combustion methods. Because the fuel in the combustion chamber is always in a lean state, the combustion chamber is more likely to be blown out by the high-speed airflow, resulting in narrowing of the combustion stability area of the combustion chamber.

In order to ensure that the gas turbine can work stably for a long time, an extremely complex combustion chamber control system must be designed in view of the narrowing of the combustion stability area of the combustion chamber, and strict requirements are placed on the control accuracy and response speed of the control system. When gas turbine components are upgraded, components are removed, installed or replaced, components are overhauled, fuel composition changes, etc., the stability region of the gas turbine combustor will change. At this time, complex combustion adjustment tests are required for the gas turbine to ensure combustion. The combustion chamber works in the middle of the combustion stable area, so the safety and reliability of the gas turbine completely depend on the combustion adjustment and control technology of the combustion chamber.

At present, the gas turbine based on isobaric combustion mainly has the following problems: 1. The structure of the combustion chamber is complex; 2. The cooling system of the combustion chamber is complicated, requiring a large amount of air to cool it, and the proportion of air actually participating in the combustion is small; 3. The stable combustion area of the combustion chamber Narrow, easy to flame out, requires a complex flame stabilization structure to stabilize the combustion chamber flame; 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 thermal cycle is limited by the high temperature resistant materials of the turbine.

【Content of invention】

The purpose of the present invention is to solve the problems existing in the existing ground gas turbines, such as the complex structure of the combustion chamber, the small proportion of air actually participating in the combustion, the narrow combustion stable area, the easy flameout and the need for frequent combustion adjustments, etc. The ground gas turbine used in the ground gas turbine has a simple structure, no cooling air film hole structure, and no complicated flame stabilizer; the combustion chamber does not need cooling air, and the compressed air can all participate in the combustion; the flame in the combustion chamber propagates at supersonic speed, no There are problems of combustion stability and flameout, and there is no need to conduct combustion adjustment tests on the combustion chamber, and the emission of combustion pollutants is low; in addition, the combustion process has the characteristics of self-pressurization, so it can reduce the number of stages of the compressor, reduce the power consumption of the compressor, and increase Power generation, improve cycle thermal efficiency.

To achieve the above object, the present invention adopts the following technical solutions:

A ground gas turbine utilizing pulse detonation combustion, comprising a compressor, a gas storage chamber, a plurality of gas supply pipelines, a plurality of pulse detonation combustors, a pressure shaping chamber, a turbine, a rotor and a tail nozzle; wherein the compressor is set At the front end of the ground gas turbine, the gas outlet of the compressor is connected to the gas storage chamber, the pressure shaping chamber, the turbine and the tail nozzle in sequence. Connected with the turbine, one end of the rotor is led out from the tail nozzle; multiple pulse detonation combustion chambers are arranged between the gas storage chamber and the pressure shaping chamber, and are evenly arranged in a ring with the rotor as the center, and the outlets of the gas storage chambers are respectively The inlets of multiple pulse detonation combustion chambers are connected through the gas supply pipeline, and the outlets of multiple pulse detonation combustion chambers are respectively connected with the inlets of the pressure shaping chambers. The circumference of a single pulse detonation combustion chamber is provided with spark plugs and fuel pipelines .

The further improvement of the present invention is that a plurality of pulse detonation combustors are installed obliquely on the periphery of the gas storage chamber of the gas turbine in the shape of an annular tube, and the pulse detonation combustors are cylindrical combustors with equal cross-sections, including combustor heads connected in sequence End cover, combustion chamber ignition section, combustion chamber detonation section, combustion chamber detonation section and combustion chamber transition section; wherein, the end cover of the combustion chamber head is provided with a main nozzle, and the main nozzle is provided with a main nozzle gas path and a main nozzle fuel Pipeline, combustion chamber detonation section and combustion chamber detonation section are provided with 3 to 8 auxiliary nozzles at equal intervals, and auxiliary nozzles are provided with auxiliary nozzle gas path and auxiliary nozzle fuel pipeline; spark plug is set at the ignition section of combustion chamber Circumferentially, the air supply pipeline is respectively connected with the main nozzle air passage and 3 to 8 auxiliary nozzle air passages through the air distributor arranged at the outlet end, and on the pipeline where the air distributor is respectively connected with several auxiliary nozzle air passages All are equipped with an auxiliary nozzle air switch solenoid valve, and the outlet of the transition section of the combustion chamber is connected to the inlet of the pressure shaping chamber.

The further improvement of the present invention lies in that: a helical reinforced detonation structure is provided in the circumferential direction inside the detonation section of the combustion chamber.

The further improvement of the present invention lies in that: the lead-out end of the rotor is connected with the generator assembly through the transmission.

The further improvement of the present invention lies in that air flow regulating valves and air flow meters are arranged on multiple air supply pipelines.

The further improvement of the present invention is that: the tail nozzle is a right-angle elbow nozzle.

The further improvement of the present invention lies in that: the end of the gas storage chamber is provided with a deflation bypass, and a high-frequency electromagnetic valve for controlling the switch of the deflation bypass is provided on the deflation bypass.

The further improvement of the present invention is that: the inlet of the gas storage chamber is an expanding annular channel, the subsonic gas flow at the outlet of the compressor is decelerated and pressurized after passing through the expanding annular channel, and the main part of the air storage chamber is an annular cavity with equal cross-section.

The further improvement of the present invention lies in that the pressure shaping chamber includes casing I, and the inside of casing I is divided into multiple annular passages by multiple annular partitions I of different lengths, and the multiple annular passages are reinforced by cross-shaped partition brackets I.

The further improvement of the present invention lies in that the pressure shaping chamber includes casing II, and inside the casing II is divided into a plurality of expanding or converging annular passages by a plurality of annular partitions II with equal axial lengths, and the plurality of annular passages pass through the cross-shaped partitions Stent II is strengthened.

Compared with the prior art, the present invention has the following technical effects:

Compared with the traditional ground gas turbine, the present invention has the advantages of self-pressurization, fast flame propagation speed (generally on the order of 10 ³ m/s), high combustion efficiency and low pollutant emission due to the pulse detonation combustion, so the present invention adopts After the pulse detonation combustor replaces the traditional isobaric combustor, the gas turbine can greatly reduce the number of stages of the compressor and the compression work of the compressor, thereby increasing the proportion of the output shaft power of the turbine for power generation, and improving the cycle thermal efficiency of the gas turbine as a whole ;

Because the pulse detonation combustion propagation velocity is on the order of 10 ³ m/s, the combustible mixture in the combustion chamber burns and releases heat instantly under the action of the detonation combustion wave, the combustion efficiency is high, and there is no problem of combustion stability and easy flameout. The invention can successfully solve the problems of narrowing of the combustion stable area of the combustion chamber and easy flameout after adopting low-pollution combustion technology in traditional gas turbines;

Because the pulse detonation combustion does not have the problems of combustion stability and flameout, the present invention can greatly reduce the combustion control system of the combustion chamber, and can save the test procedure of frequent combustion adjustment in the traditional gas turbine; at the same time, the pulse detonation combustion is A kind of homogeneous premixed combustion, and its combustion speed is very fast, and the residence time of combustion products in the high temperature area is very short, which can greatly reduce the emission of pollutants such as NOx and CO; in addition, due to the periodic intermittent nature of pulse detonation combustion , the combustor and turbine blades are not always in the harsh working environment of high temperature and high pressure gas, so the requirements for the material and cooling technology of the combustor are relatively low. Compared with the existing gas turbine, the combustor of the gas turbine after pulse detonation combustion is used and turbine blades are no longer temperature-limited.

【Description of drawings】

Fig. 1 is a kind of overall structure diagram of the ground gas turbine utilizing pulse detonation combustion of the present invention;

Fig. 2 is the schematic sectional view of the combustor of the ground gas turbine of the present invention;

Fig. 3 is the structural diagram of the first scheme of the pressure shaping chamber of the ground gas turbine of the present invention;

Fig. 4 is the A-A direction view of Fig. 3;

Fig. 5 is the structural diagram of the second scheme of the pressure shaping chamber of the ground gas turbine of the present invention;

Fig. 6 is a B-B arrow view of Fig. 5 .

Among them: 1. Air compressor; 2. Air storage chamber; 3. Air supply pipeline; 4. Air flow regulating valve; 5. Air distributor; 6. Auxiliary nozzle air switch solenoid valve; 7. Pulse detonation combustion chamber; 8 , pressure shaping chamber; 9, turbine; 10, rotor; 11, transmission; 12, generator assembly; 13, tail nozzle; 14, deflation bypass; 15, air flow meter; 16, bearing; 17, deflation Bypass switch solenoid valve; 18. Combustion gas flow path; 19. Main nozzle gas path; 20. Main nozzle; 21. Main nozzle fuel pipeline; 22. Spark plug; 23. Auxiliary nozzle; 24. Auxiliary nozzle gas path; 25 . Auxiliary nozzle fuel pipeline; 26. Spiral enhanced detonation structure; 27. Combustion chamber transition section; 28. Combustion chamber detonation section; 29. Combustion chamber initiation section; 30. Combustion chamber ignition section; 31. Combustion chamber head Department end cover; 32, clapboard bracket I; 33, annular clapboard I; 34, casing I; 35, clapboard bracket II; 36, annular clapboard II; 37, casing II.

【Detailed ways】

The present invention will be further described below in conjunction with accompanying drawing.

Referring to Fig. 1, a ground gas turbine using pulse detonation combustion according to the present invention includes a compressor 1, a gas storage chamber 2, a plurality of gas supply pipelines 3, a plurality of pulse detonation combustion chambers 7, a pressure shaping chamber 8, and a turbine 9 , the rotor 10 and the tail nozzle 13, and form the flow path of the combustion gas passing through them as shown by the arrow in FIG. 1, that is, the combustion gas flow path 18.

Among them, the compressor 1 is arranged at the front end of the ground gas turbine, the gas outlet of the compressor 1 is connected with the gas storage chamber 2, the pressure shaping chamber 8, the turbine 9 and the tail nozzle 13 in sequence, and the rotor 10 is arranged between the compressor 1 and The center of the turbine 9 is connected to the compressor 1 and the turbine 9 respectively through two bearings 16, and one end of the rotor 10 is drawn from the tail nozzle 13; a plurality of pulse detonation combustion chambers 7 are arranged in the gas storage chamber 2 and the pressure Between the shaping chambers 8, the rotor (10) is arranged uniformly in a ring shape. The outlets of the gas storage chambers 2 are respectively connected to the inlets of the multiple pulse detonation combustion chambers 7 through the gas supply pipeline 3. The multiple pulse detonation The outlets of the combustion chambers 7 are respectively connected to the inlets of the pressure shaping chambers 8 , and spark plugs 22 and fuel pipelines are arranged around the circumference of a single pulse detonation combustion chamber 7 . In use, the lead-out end of the rotor 10 is connected with the generator assembly 12 through the transmission 11 .

Referring to Fig. 2, a plurality of pulse detonation combustors 7 are installed obliquely on the periphery of the gas turbine gas storage chamber 2 in the shape of an annular tube, wherein the pulse detonation combustors 7 are cylindrical combustors with equal cross-sections, including sequentially connected combustion chambers. Chamber head end cover 31, combustion chamber ignition section 30, combustion chamber detonation section 29, combustion chamber detonation section 28 and combustion chamber transition section 27, which are curved pipe members gradually transitioning from circular to fan-shaped section; wherein, the combustion chamber The main nozzle 20 is provided on the end cover 31 of the chamber head, the main nozzle 20 is provided with the main nozzle gas passage 19 and the main nozzle fuel pipeline 21, and the combustion chamber detonation section 29 and the combustion chamber detonation section 28 are provided with 3 to 8 nozzles in the circumferential direction. Equidistant auxiliary nozzles 23, which can reduce the filling time of the pulse detonation combustion chamber 7 and improve the operating frequency of the pulse detonation combustion chamber 7. The auxiliary nozzles 23 are provided with auxiliary nozzle gas passages 24 and auxiliary nozzle fuel pipelines 25 , the inner circumference of the detonation section 28 of the combustion chamber is provided with a spiral reinforced detonation structure 26; the spark plug 22 is arranged in the circumferential direction of the ignition section 30 of the combustion chamber, and the air supply pipeline 3 is respectively connected to the main Nozzle air passage 19 is connected with several auxiliary nozzle air passages 24, and auxiliary nozzle air switch solenoid valves 6 are arranged on the pipelines where the air distributor communicates with several auxiliary nozzle air passages 24 respectively, through which the auxiliary nozzle air switch solenoid valves 6 Control the fuel supply of each auxiliary nozzle 23, and the main nozzle 20 is directly connected with the air distributor 5, that is, the main nozzle 20 is always in an open state, but because the detonation combustion has a self-pressurizing effect, when the pulse detonation combustion chamber 7 After the detonation wave is generated, the pressure in the pulse detonation combustion chamber 7 suddenly rises, and the pressure of the pulse detonation combustion chamber 7 is greater than the airflow pressure at the outlet of the main nozzle 20, so that the fuel supply of the main nozzle 20 automatically stops under the action of the pressure difference. After the shock wave is discharged from the pulse detonation combustion chamber 7, the pressure of the pulse detonation combustion chamber 7 drops rapidly, and the pressure difference drops to 0 or less, then the main nozzle 20 will automatically resume the fuel supply, that is, the main nozzle 20 always works in the self-adaptive fuel mode. Supply mode; the outlet of the combustion chamber transition section 27 is connected to the inlet of the pressure shaping chamber 8 .

Furthermore, the air supply pipeline 3 is a metal round pipe, and air flow regulating valves 4 and air flow meters 15 are installed on multiple air supply pipelines 3, which can precisely control the air flow to meet the various requirements of gas turbines under different loads. Air flow requirements for operating modes. The tail nozzle 13 is a right-angle elbow nozzle, which can change the gas flow direction by 90 degrees.

Further, the inlet of the gas storage chamber 2 is an expanding annular channel, and the subsonic gas flow at the outlet of the compressor 1 passes through the expanding annular channel and then decelerates and pressurizes. A deflation bypass 14 is provided, and a high-frequency electromagnetic valve 17 for controlling the switch of the deflation bypass 14 is provided on the deflation bypass 14 . The switch of the bleed bypass is controlled by the high-frequency solenoid valve 17. When the pulse detonation combustion chamber 7 generates a detonation wave, the excess compressed air can be directly discharged to the outlet of the combustion chamber through the bleed bypass 14.

The pressure shaping chamber 8 is located downstream of the pulse detonation combustion chamber 7. The main function of the pressure shaping chamber 8 is to shape the pulse detonation pressure wave to reduce and smooth the pressure pulsation of the pulse detonation gas. The pressure fluctuation of the small pulse detonation gas is beneficial to the energy extraction of the detonation gas by the turbine 9 .

For this reason, the present invention provides two schemes of the pressure shaping chamber. Fig. 3 is a schematic structural diagram of the first scheme of the pressure shaping chamber. The annular partition I33 divides the pressure shaping chamber 8 into four annular passages whose distance between the partitions gradually increases from the outer layer to the inner layer. The average flow velocity of the channel with the largest distance between the partitions in the pressure shaping chamber 8 is the fastest, while the average gas flow velocity of the channel with the smallest distance between the partitions is the lowest. Therefore, after passing through the pressure shaping chamber 8 of the first scheme, the single strong pulse detonation pressure wave It is decomposed into four pressure waves with sequential order in time.

Fig. 4 is a schematic structural diagram of the second scheme of the pressure shaping chamber, which is mainly composed of a variable cross-section annular partition II36 and a partition support II35 with equal axial lengths, and the three-layer annular partition II36 divides the pressure shaping chamber 8 into four Expansion or convergence deformed cross-section annular channel, because the supersonic gas flow is accelerated and decompressed in the expanded channel, and decelerated and pressurized in the convergent channel, so the supersonic gas discharged from the transition section of the pulse detonation combustion chamber passes through the pressure of the second scheme. Behind the shaping chamber 8, a single strong pulse detonation pressure wave can also be decomposed into four pressure waves with sequential order in time, so as to achieve the effect of gentle pressure shaping.

In addition, due to the self-supercharging advantage of detonation combustion, compressor 1 is the same as the traditional gas turbine compressor, but the number of stages is reduced to 2 to 3. Turbine 9 is the same as a conventional gas turbine turbine. The transmission 11 and generator assembly 12 are the same as those used in conventional gas turbines.

In order to further understand the invention, its working process is now described.

When the ground gas turbine using pulse detonation combustion of the present invention is working, the external air is sucked into the gas turbine by the compressor 1, and enters the gas storage chamber 2 after being compressed and boosted, and the compressed air is distributed by the air distributor 5 through the air supply pipeline 3 Divide into multiple streams and fuel to fill the pulse detonation combustion chamber through the combustion chamber main nozzle 20 and multi-channel auxiliary nozzle 23. After the filling is completed, the spark plug 22 at the head of the detonation chamber is ignited to form a detonation combustion wave. The detonation combustion wave starts with Supersonic propagation burns fuel and releases heat. The high-speed, high-temperature pulse detonation gas passes through the pressure shaping chamber 8 and then expands to do work through the turbine 9. The exhausted gas after expansion is finally discharged through the tail nozzle 13. The turbine work is output in the form of shaft power to The compressor 1 and the generator assembly 12 are connected through the transmission 11 between the rotor 10 and the generator assembly 12 .

More specifically, the starting air source is used to fill the pulse detonation combustion chamber, the control system issues an ignition command to ignite through the spark plug 22, and at the same time the control system issues an order to close the auxiliary nozzle air switch solenoid valve 6, and the detonation chamber forms a detonation wave and then burns The transition section 27 of the chamber enters the pressure shaping chamber 8, and the detonation gas enters the turbine 9 at high speed after being shaped and expands to do work. The turbine 9 outputs power in the form of shaft power to the compressor 1 and the generator 12. The tail nozzle 13 is discharged, the compressor 1 sucks and compresses the ambient air, the compressed air is decelerated and pressurized into the air storage chamber 2 through the expansion channel, and then supplied to each pulse detonation combustion through the air supply pipeline 3 and the air distributor 5 chamber 7, when the detonation wave spreads out of the combustion chamber, each auxiliary nozzle air switch solenoid valve 6 is opened, the main nozzle 20 and auxiliary nozzle 23 fill the combustion chamber at the same time, and after the spark plug 22 is ignited, each auxiliary nozzle air switch solenoid valve 6 is closed again , such a cycle, during this process, when the pressure of the air storage chamber 2 reaches the discharge pressure, the solenoid valve 17 of the discharge bypass switch is opened, and the compressed air is directly discharged to the transition section 27 of the combustion chamber through the discharge bypass.

Claims (7)

1. utilize a ground gas turbine for pulse detonation combustion, it is characterized in that: comprise gas compressor (1), gas storage chamber (2), multiple supply air line (3), multiple pulse detonation combustor (7), pressure shaping room (8), turbine (9), rotor (10) and jet pipe (13); Wherein, gas compressor (1) is arranged at this ground gas turbine foremost, the outlet side of gas compressor (1) is connected with jet pipe (13) with gas storage chamber (2), pressure shaping room (8), turbine (9) successively, rotor (10) is arranged at the center of gas compressor (1) and turbine (9), and be connected with turbine (9) with gas compressor (1) respectively by two bearings (16), one end of rotor (10) is drawn from jet pipe (13); Multiple pulse detonation combustor (7) is arranged between gas storage chamber (2) and pressure shaping room (8), and be evenly arranged ringwise centered by rotor (10), the outlet of gas storage chamber (2) is connected respectively by the entrance of supply air line (3) with multiple pulse detonation combustor (7), the outlet of multiple pulse detonation combustor (7) is connected with the entrance of pressure shaping room (8) respectively, individual pulse detonation combustor (7) be circumferentially with spark plug (22) and fuel conduit;

Wherein, multiple pulse detonation combustor (7) is arranged on the periphery of gas turbine gas storage chamber (2) in circular pipe type tilting, pulse detonation combustor (7) is uniform section throat less chamber, comprises the head of combustion chamber end cap (31), combustion chamber ignition section (30), the firing chamber section of detonating (29), firing chamber pinking section (28) and the firing chamber changeover portion (27) that connect successively; Wherein, head of combustion chamber end cap (31) is provided with main nozzle (20), main nozzle (20) is provided with main nozzle gas circuit (19) and main nozzle fuel conduit (21), the firing chamber section of detonating (29) and firing chamber pinking section (28) be circumferentially with 3 ~ 8 equally spaced pilot jets (23), pilot jet (23) is provided with pilot jet gas circuit (24) and pilot jet fuel conduit (25); Spark plug (22) is arranged on the circumference of combustion chamber ignition section (30), supply air line (3) is connected with 3 ~ 8 pilot jet gas circuits (24) with main nozzle gas circuit (19) respectively by the air distributor being arranged on its outlet end, and the pipeline be connected with some pilot jet gas circuits (24) respectively at air distributor is equipped with pilot jet air switching sol (6), the entrance of the outlet Bonding pressure shaping room (8) of firing chamber changeover portion (27);

The Outlet of rotor (10) is connected with generator assembly (12) by speed changer (11);

Multiple supply air line (3) is equipped with air flow rate adjustment valve (4) and Air flow meter (15).

2. a kind of ground gas turbine utilizing pulse detonation combustion according to claim 1, is characterized in that: the circumference of firing chamber pinking section (28) inner side is provided with spirality enhanced detonation structure (26).

3. a kind of ground gas turbine utilizing pulse detonation combustion according to any one of claim 1 or 2, is characterized in that: jet pipe (13) is an elbow bend jet pipe.

4. a kind of ground gas turbine utilizing pulse detonation combustion according to any one of claim 1 or 2, it is characterized in that: the end of gas storage chamber (2) is provided with venting bypass (14), and venting bypass (14) is provided with the high-frequency electromagnetic valve (17) for controlling venting bypass (14) switch.

5. a kind of ground gas turbine utilizing pulse detonation combustion according to any one of claim 1 or 2, it is characterized in that: the entrance of gas storage chamber (2) is expanssion type annular pass, gas compressor (1) outlet subsonic flow slows down supercharging behind expanssion type annular pass, and the main body of gas storage chamber (2) is prismatic annular housing.

6. a kind of ground gas turbine utilizing pulse detonation combustion according to any one of claim 1 or 2, it is characterized in that: pressure shaping room (8) comprise casing I (34), the toroidal membrane I (33) differed by multiple length in casing I (34) inside is divided into multiple annular pass, and multiple annular pass is strengthened by criss-cross bulkhead bracket I (32).

7. a kind of ground gas turbine utilizing pulse detonation combustion according to any one of claim 1 or 2, it is characterized in that: pressure shaping room (8) comprise casing II (37), casing II (37) inside is divided into multiple expansion or convergent contour annular pass by the toroidal membrane II (36) that multiple axial length is equal, and multiple annular pass is strengthened by criss-cross bulkhead bracket II (35).