A continuous rotary detonation combustion chamber and heavy gas turbine

Abstract

The application provides a continuous rotating detonation combustion chamber and a heavy gas turbine, which comprises a combustion chamber shell, a plurality of detonation nozzles are arranged in the inner cavity of the combustion chamber shell, and the detonation nozzles are fixed on the end cover of the air inlet end of the combustion chamber shell; the detonation nozzle comprises a nozzle head and a nozzle shell, the air inlet side of the nozzle head is fixedly connected with the end cover of the air inlet end of the combustion chamber shell and is used for introducing air; the nozzle shell is a through cylinder structure, the air outlet side of the nozzle head is communicated with the air inlet side of the nozzle shell; the inner cavity of the nozzle shell forms a combustion channel used for continuous rotating detonation combustion, and the side wall of the air inlet side of the nozzle shell is provided with injection holes used for injecting fuel into the combustion channel so that the fuel and air are mixed and then continuously rotate and detonate. The structure of the detonation combustion chamber is optimized, the development cost is effectively reduced, the power loss is reduced, and the equipment is convenient for later replacement and maintenance.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of gas turbine technology, in particular to a continuous rotating detonation combustion chamber and a heavy-duty gas turbine. BACKGROUND

[0002] A heavy-duty gas turbine is a heavy-duty gas turbine equipment mainly used for power generation. A gas turbine is a mechanical device that uses gas energy to generate power. It is usually composed of three parts: a gas engine, a generator and auxiliary equipment. In the gas engine, compressed gas is mixed with air and burns at high temperature. The high-temperature gas produced by combustion flows through the piston, causing the piston to move up and down, thereby driving the rotor to rotate. The generator is installed on the rotor, and the generator will also rotate when the rotor rotates, generating electricity. Auxiliary equipment includes cooling system, oil circuit system, exhaust system, etc., which helps the gas engine to work normally.

[0003] Rotating detonation combustion is a combustion technology that uses rotating detonation waves to achieve combustion. Detonation wave is a shock wave that can propagate in detonation reaction, allowing reactants and oxygen to react quickly after contact. Rotating detonation combustion is a relatively new technology that is currently used in the fields of automobiles, aviation and aerospace, mainly for improving combustion efficiency and reducing pollution.

[0004] Most of the current detonation combustion chamber structures adopt the structure of the outer ring and the inner ring. This combustion chamber structure needs to consider the cooling problems of the outer ring and the inner ring to ensure the stability of the detonation combustion. The structure design is relatively complex, the cost is high, the power loss is large, and it is not conducive to the technical upgrading and replacement of the combustion chamber structure, and the later maintenance. SUMMARY

[0005] Therefore, the present application provides a continuous rotating detonation combustion chamber and a heavy-duty gas turbine, which optimizes the structure design of the detonation combustion chamber to reduce the development cost, reduce the power loss, and facilitate the replacement and maintenance of the equipment in the later stage.

[0006] The present application provides the following technical solutions: a continuous rotating detonation combustion chamber, comprising:

[0007] A combustion chamber shell, a plurality of detonation nozzles are arranged in the inner cavity of the combustion chamber shell, and the detonation nozzles are fixed on the end cover of the gas inlet end of the combustion chamber shell;

[0008] The knock nozzle comprises a nozzle head and a nozzle shell, the air inlet side of the nozzle head is fixedly connected with the end cover of the combustion chamber shell air inlet end for introducing air; the nozzle shell is a through cylinder structure, the air outlet side of the nozzle head is communicated with the air inlet side of the nozzle shell; the inner cavity of the nozzle shell forms a combustion channel for continuous rotating detonation combustion, and the side wall of the air inlet side of the nozzle shell is provided with a spray hole for spraying fuel into the combustion channel, so that the fuel and air are mixed in the combustion channel and then continuously rotate and detonate.

[0009] According to an embodiment of the present application, in the combustion flue gas flow direction, the combustion channel comprises a combustion section, a mixing and cooling section and an exhaust section in sequence, the combustion section is used for continuous rotating detonation combustion, the inner diameter of the channel of the exhaust section is larger than that of the combustion section, and the combustion section and the exhaust section are connected through the mixing and cooling section to form a stepped connection structure.

[0010] According to an embodiment of the present application, a plurality of air film holes are uniformly arranged on the ring wall of the combustion section in the circumferential direction, for introducing air into the combustion section through the air film holes to form an air film layer on the inner wall of the combustion section.

[0011] According to an embodiment of the present application, a plurality of secondary air holes are uniformly arranged on the ring wall of the mixing and cooling section in the circumferential direction, for introducing air into the mixing and cooling section through the secondary air holes to mix the air with the detonation flue gas generated by the combustion section.

[0012] According to an embodiment of the present application, the secondary air holes are obliquely arranged on the ring wall of the mixing and cooling section, and the oblique direction of the secondary air holes is consistent with the combustion flue gas flow direction.

[0013] According to an embodiment of the present application, an outer fuel ring is fixedly arranged on the outer wall of the air inlet side of the nozzle shell in a closed manner in the circumferential direction, a fuel ring cavity for accommodating fuel is formed between the outer fuel ring and the ring wall of the nozzle shell, and the fuel ring cavity is communicated with the spray hole.

[0014] According to an embodiment of the present application, the fuel inlet of the fuel ring cavity is connected with an external fuel pipe, and the fuel is liquid hydrogen fuel.

[0015] According to an embodiment of the present application, a radial air inlet grid is arranged in the inner cavity of the air outlet side of the nozzle head, so that air enters the combustion channel after passing through the radial air inlet grid.

[0016] According to an embodiment of the present application, a plurality of knock nozzles are uniformly distributed on the end cover of the combustion chamber shell air inlet end in the circumferential direction, and are fixedly connected with the end cover through a flange.

[0017] The embodiment of the present application also provides a heavy-duty gas turbine, comprising a compressor, a continuous rotating detonation combustion chamber as described above, a transition section and a turbine.

[0018] The compressor is coaxially connected with the turbine, an air inlet of the compressor is connected with air, an air outlet of the compressor is connected with the continuous rotating detonation combustion chamber, and flue gas at an outlet of the continuous rotating detonation combustion chamber enters the turbine through the transition section to drive the turbine to work.

[0019] Compared with the prior art, the above at least one technical scheme adopted by the embodiment of the present application can achieve at least the following beneficial effects: compared with the function of atomizing fuel and mixing air of the traditional nozzle, the continuous rotating detonation combustion chamber of the embodiment of the present application improves the structure of the nozzle in the combustion chamber, so that the continuous rotating detonation combustion is directly performed in the detonation nozzle, the problem that the structure of the traditional detonation combustion chamber composed of an outer ring and an inner ring needs to simultaneously consider the cooling of the inner and outer rings is avoided, the "double-cylinder" structure is optimized to a "single-cylinder" structure, only the cooling design of the nozzle shell of the detonation nozzle needs to be implemented, the design cost is reduced, and the power loss is reduced. In addition, the single detonation nozzle is modularly developed in the embodiment, not only the cost is saved, but also different power levels of the heavy-duty gas turbine can be configured with different numbers of detonation nozzles, and the product reliability is high; the plurality of detonation nozzles are fixed with the combustion chamber shell through flanges, and the technical upgrading and replacement of the heavy-duty gas turbine or the combustion chamber structure and the later maintenance are also facilitated. BRIEF DESCRIPTION OF DRAWINGS

[0020] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly introduced as follows. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can be obtained by those skilled in the art without any creative effort on the basis of these drawings.

[0021] Figure 1 is a schematic diagram of a traditional heavy-duty gas turbine structure;

[0022] Figure 2 is a schematic diagram of a heavy-duty gas turbine structure of the embodiment of the present application;

[0023] Figure 3 is a schematic diagram of a continuous rotating detonation combustion chamber structure of the embodiment of the present application;

[0024] Figure 4 is a schematic diagram of a detonation nozzle structure of the embodiment of the present application;

[0025] Figure 5 is a schematic diagram of an internal layout of a continuous rotating detonation combustion chamber of the embodiment of the present application;

[0026] In the diagram, 1-compressor, 2-conventional combustion chamber, 3-conventional nozzle, 4-transition section, 5-turbine, 6-continuous rotating detonation combustion chamber, 601-combustion chamber shell, 7-detonation nozzle, 701-nozzle head, 702-radial intake grille, 703-nozzle shell, 704-fuel outer ring, 705-fuel annulus cavity, 706-injection hole, 707-film gas hole, 708-film gas layer, 709-secondary air hole, 710-combustion section, 711-mixing and cooling section, 712-exhaust section. Detailed Implementation

[0027] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0028] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0029] like Figure 1 As shown, Figure 1 This is a traditional heavy-duty gas turbine structure. The heavy-duty gas turbine consists of an axial compressor 1, a conventional combustion chamber 2, a conventional nozzle 3, a transition section 4, and a turbine 5. Compressed air from the compressor 1 outlet mixes and combusts with fuel from the nozzle 3 outlet in the conventional combustion chamber 2, and then enters the turbine 5 through the transition section 4 to perform work. The conventional nozzle 3 atomizes the fuel and mixes the air.

[0030] like Figures 3-4As shown, the embodiment of the present application provides a continuous rotating detonation combustion chamber 6, comprising: a combustion chamber shell 601, a plurality of detonation nozzles 7 are arranged in the inner cavity of the combustion chamber shell 601, and the detonation nozzles 7 are fixed on the end cover of the air inlet end of the combustion chamber shell 601; the detonation nozzle 7 comprises a nozzle head 701 and a nozzle shell 703, the air inlet side of the nozzle head 701 is fixedly connected with the end cover of the air inlet end of the combustion chamber shell 601, and is used for introducing air; the nozzle shell 703 is a through-cylinder structure, the air outlet side of the nozzle head 701 is in communication with the air inlet side of the nozzle shell 703; the inner cavity of the nozzle shell 703 forms a combustion channel for continuous rotating detonation combustion, a plurality of injection holes 706 are uniformly arranged on the side wall of the air inlet side of the nozzle shell 703 in the circumferential direction, and are used for injecting fuel into the combustion channel, so that the fuel and the air are mixed in the combustion channel and then continuously rotating detonation combustion occurs.

[0031] Compared with the nozzle of the traditional combustion chamber, the combustion chamber nozzle structure of the continuous rotating detonation combustion chamber 6 of the embodiment of the present application can make the continuous rotating detonation combustion directly in the detonation nozzle 7, avoid the problem that the traditional detonation combustion chamber structure composed of an outer ring and an inner ring needs to consider the cooling of the inner and outer rings, the single-cylinder combustion chamber structure saves the design of the inner ring cooling, reduces the design cost, and reduces the power loss. In addition, the embodiment modularly develops the single detonation nozzle 7, not only saves the cost, but also different power levels of heavy-duty gas turbines can be configured with different numbers of detonation nozzles 7, and the product has high reliability; the plurality of detonation nozzles 7 and the combustion chamber shell 601 can be fixed through flanges, which is convenient for technical upgrading and replacement of the heavy-duty gas turbine or the combustion chamber structure, and maintenance in the later period, and only the corresponding detonation nozzle 7 part needs to be replaced.

[0032] The rotating detonation engine is a kind of engine using detonation to organize combustion, and the combustion is organized in the circumferential direction, so that the length of the rotating detonation engine combustion chamber is lower than that of the traditional engine, and the volume and weight of the rotating detonation engine can be greatly reduced.

[0033] The working principle of the rotary detonation engine is that: firstly, air enters the detonation ring cavity from the annular channel, fuel is injected by the nozzle, and the two are uniformly mixed after a short distance and then enter the detonation ring cavity together. Then, the igniter is ignited to form an initial detonation wave in the detonation ring cavity. Secondly, the initial detonation wave propagates along the circumferential direction of the annular detonation ring cavity. Since the fuel and air flow in the axial direction, the combustion products also flow out in the axial direction. When the detonation wave propagates around the ring and returns to the initial position, the original combustion products have flowed away, and the fresh fuel and air mixture has flowed in, so the detonation wave can continue to maintain. In this way, the detonation wave continues to rotate and propagate in the annular detonation ring cavity, and the high-temperature and high-pressure combustion products are discharged at high speed through the tail nozzle, thereby generating thrust. Since the frequency of rotary detonation combustion is as high as several kilohertz, the rotary detonation engine can generate stable thrust.

[0034] In an embodiment of the present application, in the direction of the flow of combustion flue gas, the combustion channel sequentially includes a combustion section 710, a mixing and cooling section 711 and an exhaust section 712. The combustion section 710 is used for continuous rotary detonation combustion. The inner diameter of the channel of the exhaust section 712 is greater than the inner diameter of the channel of the combustion section 710. The combustion section 710 and the exhaust section 712 are connected through the mixing and cooling section 711 to form a stepped connection structure.

[0035] In the present embodiment, the combustion section 710 is the detonation combustion section of the combustion channel, and the air entering the combustion section 710 through the nozzle head 701. The fuel is injected into the combustion section 710 through the injection hole 706, and the fuel and air are mixed. After ignition by the igniter, continuous rotary detonation combustion occurs. In order to achieve detonation and produce detonation effect, the fuel burns rapidly and releases energy, so the size of the annular surface of the combustion section 710 needs to be designed to be relatively small. In terms of structure, the size of the exhaust section 712 is greater than the cross-sectional size of the combustion section 710, which is also conducive to the rapid discharge of combustion flue gas.

[0036] In order to effectively cool the combustion channel, in a further preferred embodiment, a plurality of air film holes 707 are uniformly arranged on the annular wall of the combustion section 710 in a circumferential direction, and air is introduced into the combustion section 710 through the air film holes 707, so that the air forms an air film layer 708 on the inner wall of the combustion section 710. The air entering the combustion chamber shell, part of which enters the nozzle shell 703 through the nozzle head 701 to participate in detonation combustion, and part of which surrounds the detonation nozzle 7, is introduced into the combustion section 710 through the air film holes 707 arranged on the annular wall of the combustion section 710 of the nozzle shell 703, and the air entering the combustion section 710 flows along the inner wall of the combustion section 710 and forms an air film layer 708 on the inner wall of the combustion section 710. The air film layer 708 adheres to the inner wall of the combustion section 710 as a cooling air film, forms a good cooling isolation air film, and isolates the high-temperature combustion gas. In addition, since there is also low-temperature air outside the detonation nozzle 7, combined with the air film layer 708 inside, the detonation nozzle 7 can be effectively cooled and cooled.

[0037] In an embodiment of the present application, a plurality of secondary air holes 709 are uniformly arranged on the annular wall of the mixing and cooling section 711 in a circumferential direction, and air is introduced into the mixing and cooling section 711 through the secondary air holes 709, so that the air mixes with the detonation flue gas generated by the combustion section 710.

[0038] The air introduced through the secondary air holes 709 is mainly mixed for reducing the temperature of the flue gas at the outlet of the combustion channel. After the continuous rotary detonation combustion of the combustion section 710, the temperature of the flue gas at the outlet is still very high, generally above 2000K, and the turbine cannot work at such a high temperature. Therefore, the air is introduced to cool the high-temperature flue gas, and after the air is mixed, the temperature of the flue gas is reduced to below 1200-1700K before entering the turbine, so as to ensure the normal operation of the turbine.

[0039] In a preferred embodiment of the present application, the secondary air holes 709 are arranged obliquely on the annular wall of the mixing and cooling section 711, and the oblique direction of the secondary air holes 709 is consistent with the flow direction of the combustion flue gas. The obliquely arranged secondary air holes 709 are consistent with the flow direction of the combustion flue gas, which is beneficial to the rapid and continuous stable entry of the air outside the nozzle into the mixing and cooling section 711, and ensures that the temperature of the flue gas at the outlet is within the working range of the turbine.

[0040] In one embodiment of the present application, the outer wall of the air inlet side of the nozzle shell 703 is circumferentially closed and fixed with a fuel outer ring 704, and a fuel ring cavity 705 for containing fuel is formed between the fuel outer ring and the ring wall of the nozzle shell 703, and the fuel ring cavity 705 is communicated with the injection hole 706. The fuel inlet of the fuel ring cavity 705 is connected with an external fuel pipe, fuel is injected into the fuel ring cavity 705 through the external fuel pipe, and then the fuel is injected out of the fuel ring cavity 705 through the injection hole 706, which can ensure the uniformity, continuity and stability of fuel injection, thereby ensuring the stability of detonation combustion.

[0041] In a further preferred embodiment, the fuel is liquid hydrogen fuel. The embodiment of the present application uses hydrogen as fuel for combustion, which overcomes the defect that the traditional gas turbine uses kerosene and natural gas and other fossil fuels as the main fuel, resulting in a large amount of carbon emissions during the combustion process, and achieves the purpose of zero carbon emissions. However, for a traditional conventional combustion chamber, due to the too fast flame propagation speed, the premixed combustion chamber is prone to backfire, so it is difficult to organize combustion, and the main disadvantage of using hydrogen as fuel is that the high combustion temperature and fast flame propagation speed of hydrogen can cause a substantial increase in nitrogen oxide (NOx) emissions. The embodiment of the present application simultaneously uses a rotating detonation combustion chamber structure, which can effectively reduce the generation of thermal NOx during combustion. Since hydrogen has a fast flame propagation speed, it is very suitable for rotating detonation combustion and can achieve 100% hydrogen fuel combustion. The generation of thermal NOx is a slow reaction process, which is formed by the reaction of N2 in the combustion air with reactants such as O and OH and molecular O2. Therefore, by using the characteristics of rapid detonation after ignition of the rotating detonation combustion chamber, the reaction speed is improved and the generation of thermal NOx is reduced. In addition, since the hydrogen fuel is injected in excess during rotating detonation combustion, the equivalence ratio of combustion is greater than 1, and hydrogen is in excess after combustion, which can further inhibit the generation of NOx, achieve the purpose of reducing harmful substance NOx emissions and carbon emissions, and improve combustion efficiency.

[0042] In addition, liquid hydrogen is used as fuel, and the liquid hydrogen is introduced into the fuel ring cavity 705, and the liquid hydrogen surrounds the outer wall of the combustion section 710, which can effectively cool the nozzle shell 703. At the same time, after heat exchange, the liquid hydrogen absorbs heat and is converted into gaseous hydrogen, which is then introduced into the combustion passage, so that the hydrogen fuel is used as a coolant while recovering heat for combustion, thereby reducing the combustion power and improving the combustion efficiency.

[0043] In a further preferred embodiment, a radial air inlet grid 702 is arranged in the inner cavity of the exhaust side of the nozzle head 701, so that air enters the combustion passage after passing through the radial air inlet grid 702, which can ensure that air enters the combustion passage uniformly and mixes with fuel.

[0044] In one embodiment of the present application, as shown inFigure 5 As shown, multiple knock nozzles 7 are circumferentially distributed on the end cap of the air inlet end of the combustion chamber shell 601, and are fixedly connected to the end cap via flanges. In specific implementations, different numbers of knock nozzles 7 can be configured according to different power levels of heavy-duty gas turbines.

[0045] like Figure 2 As shown in the embodiment of this application, a heavy-duty gas turbine is also provided, including a compressor 1, a continuously rotating detonation combustion chamber 6 as described above, a transition section 4, and a turbine 5; the compressor 1 and the turbine 5 are coaxially connected, air is introduced into the air inlet of the compressor 1, the air outlet of the compressor 1 is connected to the continuously rotating detonation combustion chamber 6, and the flue gas from the outlet of the continuously rotating detonation combustion chamber 6 enters the turbine 5 through the transition section 4, driving the turbine 5 to do work.

[0046] During the operation of this heavy-duty gas turbine, hydrogen fuel and air are mixed and ignited in the detonation nozzle 7 to produce high-temperature and high-pressure gas. The gas expands and accelerates in the combustion channel and is then converted into kinetic energy through the turbine components, thereby driving the generator or other equipment.

[0047] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A continuously rotating detonation combustion chamber, characterized by, include: A combustion chamber shell, wherein a plurality of knock nozzles are provided in the inner cavity of the combustion chamber shell, and the knock nozzles are fixed on the end cap at the air intake end of the combustion chamber shell; The detonation nozzle includes a nozzle head and a nozzle shell. The air intake side of the nozzle head is fixedly connected to the end cap of the air intake end of the combustion chamber shell for introducing air. The nozzle shell is a cylindrical structure that runs through the front and rear. The exhaust side of the nozzle head is connected to the air intake side of the nozzle shell. The inner cavity of the nozzle shell forms a combustion channel for continuous rotary detonation combustion. An injection hole is opened on the side wall of the air intake side of the nozzle shell for injecting fuel into the combustion channel, so that the fuel and air mix in the combustion channel and continuous rotary detonation combustion occurs. In the direction of flue gas flow, the combustion channel includes a combustion section, a mixing and cooling section and an exhaust section in sequence. The combustion section is used for continuous rotary detonation combustion. The inner diameter of the exhaust section is larger than that of the combustion section. The combustion section and the exhaust section are connected by the mixing and cooling section to form a stepped connection structure. The combustion section has multiple air film holes evenly distributed circumferentially on its annular wall, which are used to introduce air into the combustion section through the air film holes, so that the air forms an air film layer on the inner wall of the combustion section. The mixing and cooling section has multiple secondary air holes evenly distributed around its annular wall to introduce air into the mixing and cooling section, so that the air mixes with the detonation smoke generated in the combustion section.

2. The continuous rotary detonation combustion chamber of claim 1, wherein, The secondary air holes are inclinedly opened on the annular wall of the mixing and cooling section, and the inclination direction of the secondary air holes is consistent with the flow direction of the combustion flue gas.

3. The continuous rotary detonation combustion chamber of claim 1, wherein, The outer wall of the nozzle housing on the air intake side is circumferentially closed to fix the fuel outer ring. A fuel ring cavity for accommodating fuel is formed between the combustion outer ring and the ring wall of the nozzle housing. The fuel ring cavity is connected to the injection hole.

4. The continuous rotary detonation combustion chamber of claim 3, wherein, The fuel inlet of the fuel annular cavity is connected to an external fuel pipe, wherein the fuel is liquid hydrogen fuel.

5. The continuous rotary detonation combustion chamber of claim 1, wherein, A radial air intake grille is provided in the inner cavity on the exhaust side of the nozzle head, so that air enters the combustion channel after passing through the radial air intake grille.

6. The continuous rotary detonation combustion chamber of claim 1, wherein, Multiple knock nozzles are circumferentially distributed on the end cap at the air intake end of the combustion chamber shell and are fixedly connected to the end cap via flanges.

7. A heavy duty gas turbine engine characterized by, Includes a compressor, a continuously rotating detonation combustion chamber as described in any one of claims 1 to 6, a transition section, and a turbine; The compressor is coaxially connected to the turbine. Air is introduced into the compressor's inlet, and the compressor's outlet is connected to the continuous rotating detonation combustion chamber. The flue gas from the outlet of the continuous rotating detonation combustion chamber enters the turbine through the transition section, driving the turbine to perform work.

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