A pulse detonation turbine engine

Abstract

The present application provides a pulse detonation turbine engine, wherein the compressor driven by the rotating shaft comprises an impeller cover, a centrifugal impeller and a radial diffuser arranged coaxially in sequence, the first end of a plurality of tangential flow guides is embeddedly arranged on the circumferential side wall of the impeller cover, the first end side wall of the tangential flow guide is provided with a gas outlet hole for communicating the inner cavity of the tangential flow guide with the inner cavity of the impeller cover, the second end of the plurality of tangential flow guides is communicated with a plurality of detonation combustion chambers, and the plurality of detonation combustion chambers are connected with an exhaust assembly. The pulse detonation turbine engine of the present application, under the action of the radial diffuser, the outlet airflow of the compressor is changed to the circumferential direction, which can improve the atomization and mixing effect between the oil and gas, thereby shortening the required distance for detonation, and after canceling the axial diffuser, the axial length of the engine is shortened, the head region of the tangential flow guide is in a closed state, the shock wave reflection is enhanced, the detonation distance and the axial length of the engine are shortened, and the working frequency of the detonation combustion chamber is improved.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of engines, and particularly relates to a pulse detonation turbine engine. BACKGROUND

[0002] Unlike the conventional turbine engine based on isobaric combustion, the pulse detonation turbine engine adopts a pulse detonation combustion chamber to replace the conventional combustion chamber, and the combustion process thereof is similar to isochoric combustion, so that the pulse detonation turbine engine based on isochoric combustion has higher cycle thermal efficiency and unit power than the conventional turbine engine under the same engine inlet parameter condition, and the combustion process of the pulse detonation turbine engine has a self-pressurization characteristic, which can reduce the number of compressor stages and improve the power-to-weight ratio of the engine.

[0003] However, the adoption of the detonation combustion technology will also bring a series of problems. On the one hand, the deflagration wave formed by the ignition and combustion of the combustible mixture in the detonation combustion chamber needs to be gradually developed into a stable detonation wave through the action of a shock wave, which leads to a significant increase in the axial length of the detonation combustion chamber compared with the conventional combustion chamber.

[0004] On the other hand, the current pulse detonation turbine engine or pulse detonation combustion chamber generally adopts an axial air inlet and axial fuel supply mode, so that an axial diffuser is arranged at the front end of the pulse detonation combustion chamber 3 to deflect the airflow to flow along the axial direction, which directly increases the axial length of the engine, increases the airflow flow loss, and leads to an increase in the weight of the engine. At the same time, after the axial air inlet and fuel supply mode is adopted, the mutual shearing action between the air and the fuel is weakened, the atomization and mixing effect between the air and the fuel is poor, the ignition and detonation difficulty and distance are increased, which is not conducive to improving the performance of the engine. In addition, after the axial air inlet is adopted, the pressure counter-transmission exists after the generation of the detonation wave, which will affect the normal operation of the upstream compressor, leading to a longer filling air time in each cycle in the detonation combustion chamber, and making it difficult to improve the working frequency of the detonation combustion chamber. SUMMARY

[0005] In view of the above problems, the present application provides a pulse detonation turbine engine, which comprises a compressor, a tangential flow inducer, a detonation combustion chamber, an exhaust assembly and a rotating shaft.

[0006] The compressor comprises an impeller cover, a centrifugal impeller and a radial diffuser arranged coaxially in sequence, the centrifugal impeller and the radial diffuser are sleeved on the rotating shaft and are received in the inner cavity of the impeller cover.

[0007] The plurality of tangential flow inducers are arranged in a circumferential array about the impeller cover, the first end of the tangential flow inducer is embeddedly installed on the circumferential side wall of the impeller cover, and the first end side wall of the tangential flow inducer is provided with an air outlet hole communicating the inner cavity of the tangential flow inducer with the inner cavity of the impeller cover, so that the output airflow of the radial diffuser spirally flows along the axis of the tangential flow inducer after entering the inner cavity of the tangential flow inducer.

[0008] The second end of the tangential flow inducers is connected to the input end of the detonation combustion chambers, and the output end of the detonation combustion chambers is connected to the exhaust assembly.

[0009] Further, the inner wall of the detonation combustion chamber is provided with a spiral barrier strip.

[0010] Further, the tangential flow inducer comprises a first pipe body and a second pipe body which are detachably connected at the head and tail ends, the first pipe body is embeddedly installed on the circumferential side wall of the impeller cover, the tail end of the second pipe body is connected to the detonation combustion chamber, and the side wall of the second pipe body is installed with an igniter.

[0011] Further, the side wall of the first pipe body is provided with an air outlet hole, and the inner wall of the head end of the first pipe body and the air outlet hole are kept at a predetermined distance.

[0012] Further, the side wall of the first pipe body is provided with a first guide strip and a second guide strip, the tail end of the first guide strip and the tail end of the second guide strip are connected to the front side and the rear side of the air outlet hole respectively, the head end of the first guide strip and the head end of the second guide strip extend into the inner cavity of the impeller cover, so that a guide channel is formed between the first guide strip and the second guide strip.

[0013] Further, the head end of the first guide strip is in butt joint with the outer extension end of the blade of the radial diffuser.

[0014] Further, the side wall of the first guide strip and the side wall of the second guide strip facing the guide channel are both in a curved surface structure.

[0015] Further, the impeller cover comprises a end cover, a cover plate and a bottom plate which are connected in sequence, the end cover, the cover plate and the bottom plate jointly form an inner cavity for accommodating the centrifugal impeller and the radial diffuser, and a plurality of air outlet holes are arranged in the circumferential side wall of the cover plate.

[0016] Further, the exhaust assembly comprises a fuel nozzle, a fuel ring and an oil inlet;

[0017] The fuel nozzle is embeddedly installed in the first end of the tangential flow inducer, the output end of the fuel nozzle is inserted into the inner cavity of the tangential flow inducer from the end of the first end of the tangential flow inducer, the input end of the fuel nozzle is connected to one side of the fuel ring, the other side of the fuel ring is connected to a plurality of oil inlets, and the oil inlets are arranged in a staggered manner with the fuel nozzle.

[0018] Further, the exhaust assembly comprises an exhaust transition section and an exhaust mixing section, the input end of the exhaust transition section is connected to the output end of the detonation combustion chamber in a one-to-one correspondence, and the output end of the exhaust transition section is connected to the side wall of the exhaust mixing section.

[0019] Compared with the prior art, the embodiments of the present application have at least the following advantages:

[0020] 1. The pulse detonation turbine engine of the present application, the compressor outlet airflow is changed to circumferential direction under the action of the radial diffuser, and the tangential flow inducer is arranged in accordance with the airflow direction to minimize the airflow flow loss, the airflow flows downstream along the circumferential direction after flowing into the detonation combustion chamber, at this time, the air and fuel have a speed difference, and the flow directions of the air and fuel are inconsistent, the shear force between the air and fuel is enhanced under the action of centrifugal force, which is beneficial to improve the atomization and mixing effect between the air and fuel, reduce the ignition difficulty, and further shorten the required distance for detonation;

[0021] 2. After canceling the axial diffuser, the detonation combustion chamber is further moved forward, further shortening the axial length of the engine as a whole, reducing the weight of the engine, and improving the power-to-weight ratio;

[0022] 3. The circumferential opening air inlet mode is adopted, so that the head region of the tangential flow inducer forms a closed state, thereby enhancing the shock wave reflection, which can effectively promote detonation initiation and shorten the detonation distance, further shorten the axial length of the engine; at the same time, the influence of pressure back transmission on the upstream compressor is reduced, thereby the working frequency of the detonation combustion chamber can be improved, and the further engineering practical application of the pulse detonation turbine engine is promoted.

[0023] Other features and advantages of the present application will be set forth in the following description, and in part will become apparent from the description, or can be learned by practice of the present application. The objects and other advantages of the present application can be realized and obtained by the structure indicated in the specification and drawings. BRIEF DESCRIPTION OF DRAWINGS

[0024] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or prior art description. Obviously, the drawings in the following description are some embodiments of the present application, and those skilled in the art can also obtain other drawings according to these drawings without creative labor.

[0025] Figure 1 A cross-sectional structure schematic diagram of a conventional turbine engine is shown;

[0026] Figure 2 A cross-sectional structure schematic diagram of a conventional pulse detonation turbine engine is shown;

[0027] Figure 3 A cross-sectional structure schematic diagram of a pulse detonation turbine engine in an embodiment of the present application is shown;

[0028] Figure 4 A three-dimensional schematic diagram of a pulse detonation turbine engine in an embodiment of the present application is shown;

[0029] Figure 5A cross-sectional view of the compressor in the embodiment of the present application is shown Figure 1 ;

[0030] Figure 6 A cross-sectional view of the compressor in the embodiment of the present application is shown Figure 2 ;

[0031] Figure 7 A cross-sectional view of the tangential inducer in the embodiment of the present application is shown.

[0032] In the figure, the compressor 1', the radial diffuser 2', the axial diffuser 3', the combustion chamber 4', the turbine 5', the rotating shaft 6', the detonation combustion chamber 7';

[0033] The compressor 1, the radial diffuser 101, the impeller cover 102, the end cover 1021, the cover plate 1022, the bottom plate 1023, the air bleed 1024, the centrifugal impeller 103, the tangential inducer 2, the first pipe body 201, the second pipe body 202, the first guide strip 203, the second guide strip 204, the igniter 205, the detonation combustion chamber 3, the exhaust assembly 4, the exhaust transition section 401, the exhaust mixing section 402, the air outlet hole 5, the spiral obstacle strip 6, the fuel nozzle 7, the fuel ring 8, the oil inlet 9, the rotating shaft 10. DETAILED DESCRIPTION

[0034] The following description provides many different embodiments, or examples, for implementing different features of the application. Specific examples are described in the following detail so as to provide a thorough understanding of the application. The description and specific examples are not intended to limit the application in any way.

[0035] In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the following will clearly and completely explain the technical solutions in the embodiments of the present application with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are some but not all of the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall into the protection scope of the present application.

[0036] It should be noted that the conventional turbine engine structure is shown in Figure 1 , which includes the compressor 1', the radial diffuser 2', the axial diffuser 3', the combustion chamber 4', the turbine 5', the rotating shaft 6';

[0037] The working principle of the conventional turbine engine is that external air is compressed by the compressor 1', and the temperature and pressure of the air are increased, and the air flow at the outlet of the compressor 1' has a circumferential velocity, and the direction of the air flow at the outlet is finally axial after passing through the radial diffuser 2' and the axial diffuser 3', a part of the air flows into the space between the combustion chamber 4' and the casing for cooling and sealing, and the other part of the air flows into the combustion chamber 4', is mixed with the sprayed fuel, is ignited and burned, and the high-temperature gas generated is discharged to the turbine 5' and impacts the turbine to generate power, and the power is used to drive the compressor 1' and the accessory transmission device, and finally the high-temperature gas is discharged to the external atmosphere.

[0038] However, the conventional turbine engine is based on constant pressure combustion, and the component efficiency and cycle efficiency have basically reached the limit and cannot be further improved to greatly improve the engine performance, and the pulse detonation turbine engine is approximately based on constant volume combustion and has higher cycle thermal efficiency and lower fuel consumption than the constant pressure combustion in theoretical analysis.

[0039] Reference Figure 2 When the detonation combustion technology is applied to the conventional turbine engine, the conventional pulse detonation turbine engine formed has the difference from the conventional turbine engine in that the conventional constant pressure combustion chamber is replaced by the detonation combustion chamber 7', and the detonation combustion chamber generally adopts a multi-tube arrangement, and the other components are basically the same.

[0040] The working principle of the pulse detonation turbine engine is that external air is mixed with fuel to form combustible premixed gas, the combustible premixed gas is ignited and burned in the detonation combustion chamber 7' to generate a shock wave, the gas is pressurized, high-temperature and high-pressure gas is formed, the gas then impacts the turbine to generate power, and finally the gas is discharged to the external atmosphere.

[0041] In Figure 2 In the example, after the detonation combustion chamber 7' is adopted, the detonation distance of the liquid fuel is long, which leads to the excessive length of the axial length of the engine and the increase of the weight of the engine, and is not conducive to improving the power-to-weight ratio of the engine.

[0042] Meanwhile, the existing detonation combustion chamber 7' adopts an axial air inlet and an axial fuel supply mode, so that the axial diffuser 3' is arranged at the front end of the detonation combustion chamber 7' to make the air flow in the axial direction, but when the axial mode is adopted, the shearing action between the air and the fuel is weak, which leads to poor atomization and mixing effect and is not conducive to detonation initiation. And under the condition of axial air supply, the existing detonation combustion chamber 7' has pressure back transmission after the detonation wave is generated, which will affect the normal work of the upstream compressor 1', lead to the increase of the filling air time in a single cycle, and reduce the working frequency of the detonation combustion chamber 7'.

[0043] In order to solve the above problems, the present application provides a pulse detonation turbine engine, Figure 3A cross-sectional structure schematic diagram of a pulse detonation turbine engine in the embodiment of the present application is shown, Figure 3 In the present application, the pulse detonation turbine engine comprises: a compressor 1, a tangential flow guide 2, a detonation combustion chamber 3, an exhaust assembly 4, and a rotating shaft 10.

[0044] The compressor 1 comprises, in sequence, an impeller cover 102, a centrifugal impeller 103, and a radial diffuser 101, the centrifugal impeller 103 and the radial diffuser 101 are sleeved on the rotating shaft 10 and are received in the inner cavity of the impeller cover 102.

[0045] A plurality of the tangential flow guides 2 are arranged in a circumferential array about the impeller cover 102, the first end of the tangential flow guide 2 is inlaidly mounted on the circumferential sidewall of the impeller cover 102, and the first end sidewall of the tangential flow guide 2 is provided with an air outlet hole 5 that communicates the inner cavity of the tangential flow guide 2 with the inner cavity of the impeller cover 102, so that the output airflow of the radial diffuser 101 spirally flows along the axial centerline of the tangential flow guide 2 after entering the inner cavity of the tangential flow guide 2.

[0046] The second end of each of the plurality of tangential flow guides 2 corresponds to the input end of each of the plurality of detonation combustion chambers 3, and the output end of each of the plurality of detonation combustion chambers 3 is connected to the exhaust assembly 4.

[0047] In the present application, the outlet airflow of the compressor 1 is changed to the circumferential direction under the action of the radial diffuser 101, and the tangential flow guide 2 is arranged in accordance with the airflow direction to minimize the airflow loss, and the airflow flows downstream along the circumferential direction after flowing into the detonation combustion chamber 3, at this time, the air and the fuel have a speed difference, and the flow directions of the air and the fuel are inconsistent, the shear force between the air and the fuel is enhanced under the action of the centrifugal force, which is beneficial to improve the atomization and mixing effect between the air and the fuel, reduce the ignition and detonation difficulty, and further shorten the required distance for detonation.

[0048] Meanwhile, after canceling the axial diffuser, the detonation combustion chamber 3 is further moved forward, which further shortens the axial length of the whole engine, reduces the weight of the engine, and improves the power-to-weight ratio.

[0049] In addition, the head of the detonation combustion chamber 3 in the present application adopts a circumferential opening air inlet mode, and the tangential flow guide 2 is arranged in accordance with the airflow direction, so that the airflow flows backward along the circumferential direction in the detonation combustion chamber after passing through the tangential flow guide 2; at the same time, the head region of the tangential flow guide 2 forms a closed state, thereby enhancing the shock wave reflection, effectively promoting the detonation initiation, shortening the detonation distance, further shortening the axial length of the engine; at the same time, reducing the influence of pressure back transmission on the upstream compressor 1, thereby improving the working frequency of the detonation combustion chamber 3 and promoting the further engineering practical application of the pulse detonation turbine engine.

[0050] Reference Figure 3 and Figure 7The inner wall of the detonation combustion chamber 3 is provided with a spiral obstacle strip 6 for facilitating detonation initiation.

[0051] In Figure 4 In the shown example, the tangential flow inducer 2 comprises a first pipe body 201 and a second pipe body 202 detachably connected at the head and tail ends. For example, the tail end of the first pipe body 201 and the head end of the second pipe body 202 are respectively provided with flange pieces that are adapted to each other, and the flange pieces of the first pipe body 201 and the second pipe body 202 are fixed by bolts, facilitating assembly and disassembly of the tangential flow inducer 2.

[0052] The first pipe body 201 is embeddedly installed on the circumferential sidewall of the impeller cover 102, and the tail end of the second pipe body 202 is communicated with the detonation combustion chamber 3. On the basis of the airflow guiding effect of the first pipe body 201, the second pipe body 202 extends the space to provide a mixing interval for subsequent fuel and air mixing, facilitating the formation of mixed fuel. At the same time, an igniter 205 is installed on the sidewall of the second pipe body 202 to facilitate ignition of the mixed fuel.

[0053] The first pipe body 201 is embeddedly installed on the circumferential sidewall of the impeller cover 102, and the tail end of the second pipe body 202 is communicated with the detonation combustion chamber 3. On the basis of the airflow guiding effect of the first pipe body 201, the second pipe body 202 extends the space to provide a mixing interval for subsequent fuel and air mixing, facilitating the formation of mixed fuel. At the same time, an igniter 205 is installed on the sidewall of the second pipe body 202 to facilitate ignition of the mixed fuel.

[0054] It should be noted that in the case of axial air intake, the airflow entering the combustion chamber flows axially, and the airflow directly abuts against the detonation wave, causing the engine to be unable to efficiently resist the influence of the detonation wave on the intake air, thereby greatly affecting the working frequency of the detonation chamber. That is, at a low frequency, the engine produces insufficient continuous thrust, thereby limiting the practical application of the detonation turbine engine.

[0055] Reference Figure 5 , Figure 6 and Figure 7 The sidewall of the first pipe body 201 is provided with a first guide strip 203 and a second guide strip 204, the tail ends of the first guide strip 203 and the second guide strip 204 are respectively connected to the front and rear sides of the air outlet hole 5, and the head ends of the first guide strip 203 and the second guide strip 204 extend into the inner cavity of the impeller cover 102, so that a guide channel is formed between the first guide strip 203 and the second guide strip 204.

[0056] It should be noted that the radial diffuser 101 is composed of a plurality of circumferentially arrayed blades, and the airflow channels of the radial diffuser 101 are formed between adjacent blades, and the airflow flows radially along the airflow channels.

[0057] In the present invention, the guide channel corresponds to the airflow channel of the radial diffuser 101 , thereby improving the smoothness of the airflow flowing out of the airflow channel and into the guide channel.

[0058] At the same time, in order to improve the tightness of the connection between the guide channel and the airflow channel of the radial diffuser 101, the head end of the first guide strip 203 is connected to the outer end of the blade of the radial diffuser 101, shortening the distance between the first guide strip 203 and the radial diffuser 101 and ensuring the amount of airflow flowing into the guide channel.

[0059] Correspondingly, the side walls of the first guide bar 203 and the second guide bar 204 facing the guide channel both adopt a curved surface structure, so that the side walls of the first guide bar 203 and the second guide bar 204 facing the guide channel form a curved surface transition with the inner wall of the tangential flow director 2.

[0060] The impeller cover 102 includes an end cover 1021, a cover plate 1022, and a base plate 1023 connected in sequence. The end cover 1021, the cover plate 1022, and the base plate 1023 together form an inner cavity for accommodating the centrifugal impeller 103 and the radial diffuser 101. The sidewall of the cover plate 1022 is provided with a plurality of vents 1024 arranged in a circumferential array. The vents 1024 are used to release air that has not entered the combustion chamber to participate in combustion, and to release excess gas to the outside of the detonation combustion chamber 3. While ensuring sufficient air entering the detonation combustion chamber 3, it is also necessary to prevent the air flow from flowing disorderly outside the detonation combustion chamber 3. It should be noted that the position, size, number, and structural form of the vents 1024 are not limited in the present invention. Those skilled in the art can comprehensively consider the connection principle of the present invention and the actual application situation, as long as the principle of the present invention can be implemented.

[0061] In addition, this embodiment also includes a fuel nozzle 7, a fuel ring pipe 8 and a fuel inlet 9;

[0062] The fuel nozzles 7 are embedded in the first ends of the tangential flow directors 2 in a one-to-one correspondence. The output ends of the fuel nozzles 7 are inserted into the inner cavity of the tangential flow directors 2 from the first ends of the tangential flow directors 2. The fuel nozzles 7 are coaxially arranged with the tangential flow directors 2 in a one-to-one correspondence.

[0063] The input ends of the plurality of fuel nozzles 7 are commonly connected to one side of the fuel ring tube 8, and the other side of the fuel ring tube 8 is connected to a plurality of oil inlets 9, and the oil inlets 9 and the fuel nozzles 7 are staggered. When the external fuel enters the inner cavity of the fuel ring tube 8 through the oil inlet 9, and then enters the inner cavity of the tangential flow guider 2 through the fuel nozzle 7, the distribution to each detonation combustion chamber 3 is finally completed; through the staggered arrangement of the oil inlet 9 and the fuel nozzle 7, the consistency of the oil output of the plurality of fuel nozzles 7 is guaranteed, and the excessive injection pressure of a single fuel nozzle 7 is avoided, which affects the service life of the fuel nozzle 7 and the normal operation of the engine.

[0064] Exemplarily, the fuel nozzle 7 in the application is arranged at the head of the tangential flow guide 2, and the fuel sprayed by the fuel nozzle 7 has a certain atomization cone angle, which is 15°-80°, so as to have a shearing action with air. Although the above is exemplarily described by taking the coaxial arrangement of the fuel nozzle 7 and the tangential flow guide 2 as an example, the arrangement position and structure form of the fuel nozzle 7 in the application are not limited, which can be a pneumatic atomizing nozzle, a pressure atomizing nozzle or the like. Those skilled in the art can comprehensively consider according to the principle of the application and the actual application situation, as long as the principle of the application can be realized.

[0065] In the embodiment, the exhaust assembly 4 includes exhaust transition sections 401 and an exhaust mixing section 402, the input ends of the exhaust transition sections 401 are connected to the output ends of the detonation combustion chambers 3 one by one, the output ends of the exhaust transition sections 401 are connected to the same side of the exhaust mixing section 402, and the other side of the exhaust mixing section 402 is connected to turbine blades. Exemplarily, the exhaust mixing section 402 in the application is annular, and can also be in other forms. The high-temperature and high-pressure gas formed by combustion is cooled by the exhaust transition sections 401 and the exhaust mixing section 402, and then is discharged to the turbine, so as to reduce the thermal load borne by the turbine blades.

[0066] Reference Figure 3 The working principle of the application is as follows:

[0067] The impeller cover 102 intake port and the outer wall of the rotating shaft 10 are arranged in a spaced manner to form an air inlet channel. The outside air flows into the centrifugal impeller 103 through the air inlet channel, is compressed to do work, and the temperature and pressure of the gas flow are increased, and the gas flow has a certain circumferential velocity. After the gas flow passes through the radial diffuser 101, the gas flow is completely changed into circumferential flow. Part of the gas flow flows into the outside of the detonation combustion chamber 3 through the air outlet 1024 on the cover plate 1022, and the part of the gas flow can be used for cooling the detonation combustion chamber 3, cooling the turbine blades, and sealing the bearing cavity, etc. Another part of the gas flow flows into the detonation combustion chamber 3 through the tangential flow guide 2, and the fuel sprayed by the fuel nozzle 7 in the second pipe body 202 is sheared, atomized and mixed with the fuel, to form a combustible premixed gas. After the combustible premixed gas is filled, ignition is performed, a deflagration wave is generated in the initial stage of combustion, a reflected shock wave is formed after the deflagration wave hits the wall of the detonation combustion chamber 3 and the obstacle, and under the action of the continuously superimposed shock wave, a stable detonation wave is developed at a certain position in the detonation combustion chamber 3, and finally high-temperature and high-pressure gas is formed.

[0068] The detonation wave propagates to both ends, and the detonation wave propagating downstream impacts the turbine blades through the exhaust transition sections 401 and the exhaust mixing section 402, and the generated power is transmitted through the rotating shaft 10 to drive the compressor 1 and the accessory transmission device. Finally, the high-temperature and high-pressure gas is discharged into the outside atmosphere.

[0069] At the same time, the detonation wave propagating upstream has a higher pressure than the gas pressure at the outlet of the radial diffuser 101, and temporarily blocks the outlet of the radial diffuser 101; after the gas is discharged from the detonation combustion chamber 3, an expansion wave is generated at the outlet of the detonation combustion chamber 3 and propagates upstream, and after reaching the head of the detonation combustion chamber 3, the pressure at this position gradually decreases, until the outlet airflow of the compressor 1 can smoothly flow into the detonation combustion chamber 3 through the tangential flow guide 2, at which time the detonation combustion chamber 3 starts the next cycle.

[0070] It should be noted that the present application can be applied to different types of engines such as turboshaft, turboprop, turbojet and turbofan. When applied to turboshaft and turboprop engines, the engine has a power output shaft, which transmits power to drive accessories, rotors, etc. through the shaft; when applied to turbojet or turbofan engines, it does not need to have a power output shaft.

[0071] In the description of the present application, the terms "first", "second" are only for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first", "second" can explicitly or implicitly include one or more of the features. In the description of the present application, the meaning of "a plurality of" is two or more, unless otherwise specifically limited.

[0072] In the description of the present application, it should be noted that, unless otherwise specifically specified and limited, the terms "mounting", "connecting", "connection" should be understood in a broad sense, for example, it can be fixed connection, or detachable connection, or integrally connected; it can be mechanical connection, or electrical connection or can communicate with each other; it can be directly connected, or indirectly connected through an intermediate medium, or the communication between multiple elements or the interaction relationship between multiple elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0073] In the description of the present application, it should be understood that all the terms used to indicate the orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, which is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element indicated must have a specific orientation, be constructed and operated in a specific orientation, and cannot be understood as a limitation of the present application.

[0074] Although the present application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that the technical solutions recorded in the foregoing embodiments can still be modified, or some technical features can be replaced by equivalents; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present application.

Claims

1. A pulse detonation turbine engine, characterized by, The utility model relates to a turbofan engine, including: A compressor (1), a tangential flow guide (2), a knock combustion chamber (3), an exhaust assembly (4), a rotating shaft (10); The compressor (1) includes impeller cover (102), centrifugal impeller (103) and radial diffuser (101) arranged coaxially in sequence, and the centrifugal impeller (103) and radial diffuser (101) are sleeved on the rotating shaft (10) and are received in the inner cavity of the impeller cover (102); A plurality of tangential flow guides (2) are arranged in a circumferential array about the impeller cover (102), the first end of the tangential flow guide (2) is inlaidly installed on the circumferential side wall of the impeller cover (102), the second end of a plurality of tangential flow guides (2) one by one corresponds to the input end of a plurality of knock combustion chambers (3), and the output end of a plurality of knock combustion chambers (3) is connected to the exhaust assembly (4); The tangential flow guide (2) includes a first pipe body (201) and a second pipe body (202) detachably connected at the first end and the tail end, the first pipe body (201) is inlaidly installed on the circumferential side wall of the impeller cover (102), the tail end of the second pipe body (202) communicates with the knock combustion chamber (3), the side wall of the first pipe body (201) is provided with an air outlet hole (5) communicating the inner cavity of the tangential flow guide (2) with the inner cavity of the impeller cover (102), so that the output gas flow of the radial diffuser (101) spirally flows along the axial line of the tangential flow guide (2) after entering the inner cavity of the tangential flow guide (2); The side wall of the first pipe body (201) is provided with a first guide strip (203) and a second guide strip (204), the tail end of the first guide strip (203) and the second guide strip (204) is connected to the front side and the rear side of the air outlet hole (5) respectively, and the head end of the first guide strip (203) and the second guide strip (204) extends to the inner cavity of the impeller cover (102), so that a guide channel is formed between the first guide strip (203) and the second guide strip (204).

2. The pulse detonation turbo engine of claim 1, wherein, The inner wall of the knock combustion chamber (3) is provided with a spiral obstacle strip (6).

3. The pulse detonation turbo engine of claim 1, wherein, The side wall of the second pipe body (202) is provided with an igniter (205).

4. The pulse detonation turbo engine of claim 3, wherein, The inner wall of the head end of the first pipe body (201) and the air outlet hole (5) retain a predetermined spacing.

5. The pulse detonation turbo engine of claim 4, wherein, The head end of the first guide strip (203) is in butt joint with the outer extension end of the blade of the radial diffuser (101).

6. The pulse detonation turbo engine of claim 5, wherein, The side wall of the first guide strip (203) and the second guide strip (204) facing the guide channel adopts a curved surface structure.

7. The pulse detonation turbo engine of claim 1, wherein, The impeller cover (102) includes an end cover (1021), a cover plate (1022) and a bottom plate (1023) connected in sequence, and the end cover (1021), the cover plate (1022) and the bottom plate (1023) jointly form an inner cavity for receiving the centrifugal impeller (103) and the radial diffuser (101), and a plurality of air release holes (1024) are arranged in a circumferential array on the side wall of the cover plate (1022).

8. The pulse detonation turbine engine of any one of claims 1 to 7, wherein, It also includes a fuel nozzle (7), a fuel ring (8) and an oil inlet (9). A number of said fuel nozzles (7) are one-to-one embeddedly installed at the first end of a number of tangential flow guides (2), the output end of the fuel nozzle (7) is inserted into the inner cavity of the tangential flow guide (2) from the first end of the tangential flow guide (2), the input end of a number of said fuel nozzles (7) is connected to one side of the fuel ring (8), the other side of the fuel ring (8) is connected to a number of oil inlets (9), and the oil inlets (9) are arranged in a staggered manner with the fuel nozzles (7).

9. The pulse detonation turbo engine of claim 8, wherein, The exhaust assembly (4) includes an exhaust transition section (401) and an exhaust mixing section (402), the input end of a number of said exhaust transition sections (401) is one-to-one connected to the output end of a number of detonation combustion chambers (3), and the output end of a number of said exhaust transition sections (401) is commonly connected to the side wall of the exhaust mixing section (402).

Images