Detonation combustion chamber and gas turbine

Abstract

The present invention provides a detonation combustion chamber and a gas turbine, the detonation combustion chamber comprising: a detonation combustion chamber shell, the inner cavity of the detonation combustion chamber shell is coaxially sleeved with a detonation outer ring and a detonation inner ring from the outside to the inside, the detonation outer ring and the detonation inner ring are both tubular structures, a main flow channel annular cavity for detonation combustion is formed between the annular walls of the detonation outer ring and the detonation inner ring, the air inlet end of the main flow channel annular cavity is connected to air, and the air is mixed with the fuel in the cavity for detonation combustion; a first annular cavity is arranged between the detonation combustion chamber shell and the annular wall of the detonation outer ring, and the first annular cavity is used as an outer cooling channel to pass circulating coolant; the inner cavity of the detonation inner ring is provided with an inner cooling channel, and circulating coolant is passed into the inner cooling channel. The structure of the present invention can effectively improve the cooling effect of the detonation combustion chamber, ensure the long-term stable operation of the gas engine, and improve the power adjustment range of the gas turbine, improve the combustion efficiency, and reduce the difficulty of processing.

Description

Technical Field

[0001] The present invention relates to the technical field of gas turbines, and in particular to a detonation combustion chamber and a gas turbine. Background Art

[0002] A gas turbine is a mechanical device that uses gas energy to generate power. It usually consists of three parts: a gas engine, a generator, and auxiliary equipment. In a gas engine, the gas is compressed, mixed with air, and burned at high temperatures. The high-temperature gas produced by the combustion flows through the piston, causing the piston to move up and down, thereby driving the rotor to rotate. A generator is installed on the rotor, and when the rotor rotates, the generator also rotates to generate electricity. Auxiliary equipment includes cooling systems, oil systems, exhaust systems, etc., and their function is to help the gas engine work properly. For example, the cooling system can keep the temperature of the gas engine within a suitable range; the oil system can provide lubricating oil for the gas engine; and the exhaust system can discharge the exhaust gas generated by the gas engine.

[0003] Detonation combustion is a combustion technology that achieves combustion through the propagation of a detonation wave. A detonation wave is a shock wave that can propagate in a detonation reaction, allowing the reactants and oxygen to react quickly after contact. Detonation combustion technology can be used to improve combustion efficiency, reduce pollution, and operate at higher pressures and temperatures. Detonation combustion technology is currently used in the automotive, aviation, and aerospace industries.

[0004] The existing detonation combustion chamber is difficult to arrange cooling structure due to the structural limitation of its large diameter annular cavity. Therefore, most of the existing gas engines have no cooling and cannot work for a long time. Some detonation combustion chambers with cooling structure also have problems such as poor cooling effect to varying degrees. In addition, the existing gas turbines are all single annular combustion chambers. Due to the two large diameter inner and outer ring structures, it is difficult to ensure coaxiality in processing, and it is difficult to form a narrow annular channel with uniform size of the whole ring due to the coaxiality and ellipticity. Under the working conditions of detonation combustion, after the inner and outer rings expand, the size change will make the above problems more serious and cannot work stably for a long time. Summary of the invention

[0005] In view of this, an embodiment of the present application provides a detonation combustion chamber and a gas turbine to effectively improve the cooling effect of the detonation combustion chamber, ensure the long-term stable operation of the gas engine, and increase the power adjustment range of the gas turbine, improve combustion efficiency, reduce processing difficulty, and improve precision.

[0006] The embodiment of the present application provides the following technical solution: a detonation combustion chamber, comprising:

[0007] A detonation combustion chamber shell, wherein the inner cavity of the detonation combustion chamber shell is coaxially sleeved with a detonation outer ring and a detonation inner ring in sequence from the outside to the inside, the detonation outer ring and the detonation inner ring are both tubular structures, a main flow channel annular cavity for detonation combustion is formed between the annular walls of the detonation outer ring and the detonation inner ring, and air is connected to the air inlet end of the main flow channel annular cavity for mixing air with the fuel in the main flow channel annular cavity for detonation combustion;

[0008] A first annular cavity is arranged between the detonation combustion chamber shell and the annular wall of the detonation outer ring, and the first annular cavity is used as an external cooling channel to pass circulating coolant; an inner cooling channel is arranged in the inner cavity of the detonation inner ring, and circulating coolant is passed through the inner cooling channel.

[0009] According to one embodiment of the present application, the detonation combustion chamber shell also includes a cooling inner ring, which is a columnar structure and is coaxially sleeved in the inner cavity of the detonation inner ring. The inner cooling channel is formed between the cooling inner ring and the detonation inner ring.

[0010] According to one embodiment of the present application, a second annular cavity is further arranged between the detonation combustion chamber shell and the annular wall of the detonation outer ring, the second annular cavity is arranged on the side of the first annular cavity close to the air inlet end of the main flow channel annular cavity, fuel is introduced into the second annular cavity, and a fuel injection hole is opened on the detonation outer ring in the second annular cavity, which is used to pass the fuel into the main flow channel annular cavity through the fuel injection hole.

[0011] According to an embodiment of the present application, there are multiple fuel injection holes, and they are evenly distributed circumferentially on the detonation outer ring.

[0012] According to one embodiment of the present application, on the intake end side of the main flow channel annular cavity, ridges extend toward each other between the outer wall surface of the detonation inner ring and the inner wall surface of the detonation outer ring, and an air throat is formed between the two ridges extending toward each other, so that air enters the main flow channel annular cavity after being throttled by the air throat.

[0013] According to one embodiment of the present application, a third ring cavity is further arranged between the detonation combustion chamber shell and the ring wall of the detonation outer ring, and the third ring cavity is arranged on the side of the first ring cavity away from the air inlet end of the main channel ring cavity, and cooling gas is passed into the third ring cavity. A mixed gas injection hole is provided on the detonation outer ring in the third ring cavity, which is used to pass cooling gas into the end of the main channel ring cavity through the mixed gas injection hole, so that the cooling gas is mixed with the flue gas after combustion in the main channel ring cavity and then discharged.

[0014] According to an embodiment of the present application, there are multiple mixed gas injection holes, and they are evenly distributed circumferentially on the detonation outer ring.

[0015] According to one embodiment of the present application, the circulating coolant is circulating cooling water.

[0016] An embodiment of the present application also provides a gas turbine, comprising: a gas turbine casing, wherein the gas turbine casing includes a motor, a compressor, a turbine, and a plurality of detonation combustion chambers as described above, which are coaxially connected in sequence through a main shaft, wherein the air inlet of the compressor is connected to air, the exhaust port of the compressor is connected to the air inlets of the plurality of detonation combustion chambers, and the exhaust ports of the plurality of detonation combustion chambers are connected to the turbine, thereby driving the turbine to perform work.

[0017] According to one embodiment of the present application, a plurality of detonation combustion chambers are evenly distributed circumferentially inside the gas turbine casing.

[0018] Compared with the prior art, at least one of the above-mentioned technical solutions adopted in the embodiments of this specification can achieve the following beneficial effects at least: the embodiments of the present invention improve the structure of the detonation combustion chamber, adopt a structural arrangement of a coaxial sleeve of an outer shell, a detonation outer ring and a detonation inner ring, and use the annular chamber formed between the detonation outer ring and the detonation inner ring as the main flow channel chamber for detonation combustion, while an outer cooling channel and an inner cooling channel are respectively arranged on the outer ring of the detonation outer ring and the inner ring of the detonation inner ring, which can quickly cool down the detonation combustion chamber and greatly improve the cooling effect, thereby ensuring the long-term stable operation of the detonation combustion chamber, and greatly reducing the thermal deformation caused by the increase in the combustion chamber temperature, thereby ensuring the coaxiality and accuracy of the combustion chamber annular cavity structure.

[0019] In addition, a plurality of the above-mentioned detonation combustion chambers are provided in the gas turbine of the embodiment of the present invention, and the plurality of detonation combustion chambers are arranged circumferentially. Compared with the traditional detonation combustion engine with a single large-diameter combustion chamber, the structure of the plurality of combustion chambers is convenient for cooling and can realize a wider range of power regulation of the gas turbine by controlling the opening and closing of any combustion chamber, thereby effectively improving the combustion efficiency and reducing the difficulty of processing. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0021] Figure 1 is a schematic diagram of the structure of a detonation combustion chamber according to an embodiment of the present invention;

[0022] Figure 2 is a schematic diagram of the structure of a gas turbine according to an embodiment of the present invention;

[0023] Figure 3 yes Figure 2The local schematic diagram of the A in the middle;

[0024] Among them, 1-motor, 2-compressor, 3-detonation combustion chamber, 4-turbine, 301-detonation combustion chamber casing, 302-detonation outer ring, 303-detonation inner ring, 304-first ring cavity, 305-inner cooling channel, 306-cooling inner ring, 307-second ring cavity, 308-fuel injection hole, 309-air throat, 310-third ring cavity, 311-mixed gas injection hole. DETAILED DESCRIPTION

[0025] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0026] It should be noted that, in the absence of conflict, the embodiments in this application and the features in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments, and the technical scheme of the present invention will be clearly and completely described. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0027] like Figure 1 As shown, an embodiment of the present invention provides a detonation combustion chamber, comprising:

[0028] A detonation combustion chamber shell 301, the inner cavity of which is coaxially sleeved with a detonation outer ring 302 and a detonation inner ring 303 from outside to inside in sequence, the detonation outer ring 302 and the detonation inner ring 303 are both tubular structures, a main flow channel annular cavity for detonation combustion is formed between the annular walls of the detonation outer ring 302 and the detonation inner ring 303, the air inlet end of the main flow channel annular cavity is connected to air, so as to mix the air with the fuel in the main flow channel annular cavity for detonation combustion; a first annular cavity 304 is arranged between the detonation combustion chamber shell 301 and the annular wall of the detonation outer ring 302, the first annular cavity 304 is used as an external cooling channel to pass circulating coolant; an inner cooling channel 305 is arranged in the inner cavity of the detonation inner ring 303, and circulating coolant is passed through the inner cooling channel 305.

[0029] In the embodiment of the present invention, a detonation combustion chamber shell 301, a detonation outer ring 302 and a detonation inner ring 303 are coaxially sleeved in a structural setting, and the annular chamber formed between the detonation outer ring 302 and the detonation inner ring 303 is used as a main flow channel annular cavity for detonation combustion. At the same time, a first annular cavity 304 and an inner cooling channel 305 are respectively provided on the outer ring of the detonation outer ring 302 and the inner ring of the detonation inner ring 303 as an external cooling channel, and circulating coolant is provided on both the inner and outer layers of the main flow channel annular cavity, so that the detonation combustion chamber can be quickly cooled and the cooling effect is greatly improved, so that the detonation combustion chamber can work stably for a long time, and the thermal deformation caused by the increase of the combustion chamber temperature is reduced to a great extent, thereby ensuring the coaxiality and accuracy of the combustion chamber annular cavity structure.

[0030] The structure of the inner cooling channel 305 can be implemented in a variety of cooling structures. In a preferred embodiment of the present invention, the detonation combustion chamber housing 301 further includes a cooling inner ring 306, which is a columnar structure and is coaxially sleeved in the inner cavity of the detonation inner ring 303, and the inner cooling channel 305 is formed between the cooling inner ring 306 and the detonation inner ring 303. This structural setting is simple and easy to implement, and can achieve a good cooling effect.

[0031] In other embodiments, a cooling pipe may be spirally wound on the inner cavity wall of the detonation inner ring 303 to form the inner cooling channel 305 .

[0032] In another embodiment of the present invention, a second annular cavity 307 is further arranged between the detonation combustion chamber shell 301 and the annular wall of the detonation outer ring 302. The second annular cavity 307 is arranged on the side of the first annular cavity 304 close to the air inlet end of the main flow channel annular cavity. Fuel is introduced into the second annular cavity 307. A fuel injection hole 308 is opened on the detonation outer ring 302 in the second annular cavity 307, which is used to pass the fuel into the main flow channel annular cavity through the fuel injection hole 308.

[0033] In the preferred structure, there are multiple fuel injection holes 308, which are evenly distributed circumferentially on the detonation outer ring 302 to ensure that the fuel can evenly enter the main channel annular cavity; at the same time, the fuel enters the second annular cavity 307, which can also cool the detonation combustion chamber.

[0034] In another embodiment of the present invention, on the air inlet side of the main flow channel annular cavity, convex ridges are extended toward each other between the outer wall surface of the detonation inner ring 303 and the inner wall surface of the detonation outer ring 302, and an air throat 309 is formed between the two convex ridges extending toward each other, so that air enters the main flow channel annular cavity after being throttled by the air throat 309. Figure 3The structural setting of the air throat 309 allows the air to enter the main channel annular cavity uniformly, and after the air is throttled at the throat, it realizes supersonic flow, so that the detonation wave generated by the downstream detonation combustion will not be transmitted back to the upstream compressor, thereby affecting the normal operation of the compressor.

[0035] Since the flue gas generated after detonation combustion has the characteristics of high temperature, high speed and high pressure, in order to avoid the high-temperature flue gas from affecting the turbine behind and to solve the problem that the detonation flue gas temperature is too high and the turbine cannot work, in another embodiment of the present invention, a third annular cavity 310 is further arranged between the detonation combustion chamber shell 301 and the annular wall of the detonation outer ring 302, and the third annular cavity 310 is arranged on the side of the first annular cavity 304 away from the air inlet end of the main channel annular cavity, and cooling air is passed into the third annular cavity 310, and a mixed gas injection hole 311 is provided on the detonation outer ring 302 in the third annular cavity 310, which is used to pass the cooling air into the end of the main channel annular cavity through the mixed gas injection hole 311, so that the cooling air is mixed with the flue gas after combustion in the main channel annular cavity and then discharged, so as to reduce the flue gas temperature and cool the detonation combustion chamber at the same time.

[0036] In a preferred structure, there are multiple mixed gas injection holes 311, which are evenly distributed on the detonation outer ring 302 in the circumferential direction, so as to ensure that the cooling gas can evenly enter the end of the main channel ring cavity to mix with the detonation flue gas. The cooling gas can be cooling air.

[0037] In the specific structural setting of this embodiment, three grooves may be opened circumferentially on the inner wall of the detonation combustion shell 301, and the three grooves and the detonation outer ring 302 respectively form the above-mentioned first annular cavity 304, second annular cavity 307, and third annular cavity 310. Or, three grooves may be opened circumferentially on the outer wall of the detonation outer ring, and the three grooves and the inner wall of the detonation combustion shell respectively form the above-mentioned first annular cavity 304, second annular cavity 307, and third annular cavity 310. Circulating coolant is introduced into the first annular cavity 304 for cooling the combustion chamber, fuel is introduced into the second annular cavity 307 for detonation combustion, and cooling air is introduced into the third annular cavity 310 for reducing the temperature of the detonation flue gas and cooling the combustion chamber; wherein, the circulating coolant may preferably be circulating cooling water.

[0038] The present application also provides a gas turbine, such as Figure 2As shown, the gas turbine includes: a gas turbine casing, wherein the gas turbine casing includes a motor 1, a compressor 2, a turbine 4, and a plurality of detonation combustion chambers 3 as described above, which are coaxially connected in sequence through a main shaft, wherein the air inlet of the compressor 2 is connected to air, the exhaust port of the compressor 2 is connected to the air inlets of the plurality of detonation combustion chambers 3, and the exhaust ports of the plurality of detonation combustion chambers 3 are connected to the turbine 4, so as to drive the turbine 4 to do work.

[0039] In the specific mechanical connection part, the motor 1, the compressor 2, and the turbine 4 are connected through the main shaft and work at the same speed. After being pressurized by the compressor 2, the atmospheric air enters the detonation combustion chamber 3, and after being mixed with the fuel, enters the turbine 4 through the rectifying channel to perform work.

[0040] In a preferred embodiment of the present application, a plurality of detonation combustion chambers 3 are uniformly distributed circumferentially inside the gas turbine housing. In order to realize detonation combustion, the existing detonation combustion chamber structure is designed so that the height of the combustion chamber channel can only be adjusted within a small range. Therefore, when it is applied to an engine with slightly larger power, a single narrow channel and a large-diameter circular ring structure need to be formed. The processing and manufacturing are very difficult, and the precision is difficult to ensure. Moreover, the temperature of the combustion chamber increases under working conditions, resulting in thermal deformation, which will further significantly deteriorate the coaxiality and precision of the large-diameter circular ring of the entire channel. In addition, since the working range of the detonation combustion chamber is relatively narrow, for example, when the set power is 100, the detonation combustion chamber can only realize detonation combustion within the range of 90-100, while the gas turbine needs to work stably within a larger range of 0-100. Therefore, compared with the detonation combustion engine with a traditional single large-diameter combustion chamber, the structure of multiple combustion chambers is convenient for cooling, and can realize a wider range of power regulation of the gas turbine by controlling the opening and closing of any combustion chamber, effectively improving the combustion efficiency, reducing the processing difficulty, and ensuring the structural design accuracy.

[0041] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A detonation combustion chamber, characterized in that: include: A detonation combustion chamber shell, wherein the inner cavity of the detonation combustion chamber shell is coaxially sleeved with a detonation outer ring and a detonation inner ring in sequence from the outside to the inside, the detonation outer ring and the detonation inner ring are both tubular structures, a main flow channel annular cavity for detonation combustion is formed between the annular walls of the detonation outer ring and the detonation inner ring, and air is connected to the air inlet end of the main flow channel annular cavity for mixing air with the fuel in the main flow channel annular cavity for detonation combustion; A first annular cavity is provided between the detonation combustion chamber shell and the annular wall of the detonation outer ring, and the first annular cavity is used as an external cooling channel to pass circulating coolant; an inner cooling channel is provided in the inner cavity of the detonation inner ring, and circulating coolant is passed into the inner cooling channel; A second annular cavity is further provided between the detonation combustion chamber shell and the annular wall of the detonation outer ring, the second annular cavity is provided on a side of the first annular cavity close to the air inlet end of the main flow channel annular cavity, fuel is introduced into the second annular cavity, and a fuel injection hole is provided on the detonation outer ring in the second annular cavity, for introducing fuel into the main flow channel annular cavity through the fuel injection hole; On the air inlet end side of the main flow channel annular cavity, convex ridges are respectively extended between the outer wall surface of the detonation inner ring and the inner wall surface of the detonation outer ring, and an air throat is formed between the two convex ridges extending towards each other, so that the air enters the main flow channel annular cavity after being throttled by the air throat; A third ring cavity is also arranged between the detonation combustion chamber shell and the ring wall of the detonation outer ring. The third ring cavity is arranged on the side of the first ring cavity away from the air inlet end of the main channel ring cavity. Cooling gas is passed into the third ring cavity. A mixed gas injection hole is provided on the detonation outer ring in the third ring cavity, which is used to pass cooling gas into the end of the main channel ring cavity through the mixed gas injection hole, so that the cooling gas is mixed with the flue gas after combustion in the main channel ring cavity and then discharged.

2. The detonation combustion chamber according to claim 1, characterized in that: The detonation combustion chamber shell also includes a cooling inner ring, which is a columnar structure and is coaxially sleeved in the inner cavity of the detonation inner ring. The inner cooling channel is formed between the cooling inner ring and the detonation inner ring.

3. The detonation combustion chamber according to claim 1, characterized in that: There are multiple fuel injection holes, which are evenly distributed circumferentially on the detonation outer ring.

4. The detonation combustion chamber according to claim 1, characterized in that: There are multiple mixed gas injection holes, which are evenly distributed circumferentially on the detonation outer ring.

5. The detonation combustion chamber according to claim 1, characterized in that: The circulating coolant is circulating cooling water.

6. A gas turbine, characterized in that: include: A gas turbine casing, wherein the gas turbine casing includes a motor, a compressor, a turbine, and a plurality of detonation combustion chambers as described in any one of claims 1 to 5, which are coaxially connected in sequence through a main shaft, an air inlet of the compressor is connected to air, an exhaust port of the compressor is connected to an air inlet of a plurality of the detonation combustion chambers, and an exhaust port of the plurality of the detonation combustion chambers is connected to the turbine, so as to drive the turbine to perform work.

7. The gas turbine according to claim 6, characterized in that The plurality of detonation combustion chambers are uniformly distributed circumferentially inside the gas turbine casing.

Images