An experimental setup for a radial internal combustion wave rotor turboshaft engine

Abstract

This invention discloses an experimental apparatus for a radial internal combustion wave rotor turboshaft engine, comprising a radial internal combustion wave rotor, an outer support frame, an oil ring, a casing, an intake ring, an exhaust ring, an inner support frame, first and second bearings, and first and second shaft seats. In this invention, incoming air flows in from the outside of the wave rotor combustion chamber, while high-temperature combustion gas flows out from the inside. The airflow from the compressor mixes with fuel injected from the oil ring to form a premixed gas, which flows into each set of combustion channels through intake windows with different phase differences on the intake ring. An igniter on the intake ring ignites the mixture in the combustion channels for isochoric combustion. The burned high-temperature, high-pressure gas is radially discharged from the exhaust ring and then flows axially through the curved flow channel of the curved pipe support frame, driving the turbine to perform work. This invention uses an isochoric combustion radial wave rotor instead of the isobaric combustion chamber of a traditional turboshaft engine, effectively improving the thermodynamic cycle efficiency and increasing the output power.

Description

Technical Field

[0001] This invention relates to the field of unsteady supercharging combustion technology for novel aero-engines, and in particular to an experimental apparatus for a radial internal combustion wave rotor turboshaft engine. Background Technology

[0002] With increasing energy demand, more efficient combustion-powered engine systems are becoming increasingly attractive. Among these engines, gas turbine engines remain the primary choice, playing a crucial role in applications such as ground-based power generation systems and aircraft propulsion, and continuous progress is being made in developing technologies that enhance current designs, materials, and manufacturing processes. However, due to the already excellent aerodynamic performance of turbomachinery, simply optimizing the performance of individual components to improve the overall engine performance is no longer sufficient. Therefore, improving cycle thermal efficiency can be achieved by modifying the thermodynamic cycle. Currently, a promising approach to improving the thermodynamic cycle is the internal combustion wave rotor engine, which utilizes constant-volume heating and shockwave pressurization. This engine uses unstable waves to convert energy, fundamentally improving the cycle efficiency of the gas turbine and generating more useful work.

[0003] The patent "A Simplified Internal Combustion Wave Rotor Experimental Device Based on Relative Motion", patent number: CN201410605584.5, invented an axial internal combustion wave rotor experimental device in which the channel is stationary while the sealing disk rotates, facilitating data collection; while the patent "Internal Combustion Wave Rotor Turbine Shaft Engine", patent number: CN201610873096.1, proposed to apply the internal combustion wave rotor between the compressor and the turbine to replace the traditional isobaric combustion chamber, taking into account the actual installation and fixation of the wave rotor.

[0004] Existing inventions mainly focus on the research of axial wave rotors, which have a large axial dimension. However, the space of traditional combustion chambers is limited. To replace the traditional combustion chamber structure, a more compact structure is needed. The biggest feature of radial internal combustion wave rotors is their compact structure, which can make full use of the axial distance to boost combustion and output effective power. Summary of the Invention

[0005] The technical problem to be solved by the present invention is to provide an experimental device for a radial internal combustion wave rotor turboshaft engine, which addresses the deficiencies mentioned in the background art.

[0006] To solve the above-mentioned technical problems, the present invention adopts the following technical solution:

[0007] An experimental apparatus for a radial internal combustion wave rotor turboshaft engine includes a radial internal combustion wave rotor, an outer support frame, an oil ring, a casing, an intake ring, an exhaust ring, an inner support frame, a first bearing, a second bearing, a first shaft seat, and a second shaft seat.

[0008] The radial internal combustion wave rotor includes a first rotating shaft, a combustion ring, and a second rotating shaft. The first and second rotating shafts have the same structure, being hollow cylinders open at both ends. The combustion ring is also a hollow cylinder open at both ends, with its inner wall diameter smaller than that of the first rotating shaft and its outer wall diameter larger than that of the first rotating shaft. The outer wall of the combustion ring has M rows of equidistant combustion channels penetrating its inner wall, and each row of combustion channels contains N circumferentially uniformly arranged combustion channels, where M is a natural number greater than or equal to 1 and N is a natural number greater than or equal to 2. The first rotating shaft, the combustion ring, and the second rotating shaft are coaxially fixed together in sequence.

[0009] The outer support frame includes a ring, a transition section, and a cylindrical section. The ring is circular, and the cylindrical section is a hollow cylinder with openings at both ends. The diameter of the outer wall of the cylindrical section is smaller than the diameter of the inner wall of the ring, and the cylindrical section is located downstream of the ring. The outer side of the transition section is connected to the inner wall of the ring, and the inner side is connected to one upstream end of the cylindrical section, so that the ring and the cylindrical section form an arc transition.

[0010] The casing includes an outer shell, a transition shell, and an inner shell. Both the outer shell and the inner shell are hollow cylinders with openings at both ends. The diameter of the inner wall of the outer shell is larger than the diameter of the outer wall of the inner shell. The outer side of the transition shell is sealed and coaxially fixed to the downstream end of the outer shell, and the inner side is sealed and coaxially fixed to the upstream end of the inner shell.

[0011] The inner support frame includes a fixing part and an air guiding part. The fixing part is a hollow cylinder with openings at both ends. Its outer wall diameter is equal to the inner wall diameter of the inner shell and it is coaxially fixed to the inner shell. The air guiding part is an annular ring with a U-shaped radial cross section. It is located upstream of the fixing part, and the outer end of the air guiding part is coaxially fixed to the upstream end of the fixing part, so that the opening of the air guiding part faces downstream.

[0012] The first bearing housing is fixed to the downstream end face of the outer support frame ring, and the second bearing housing is fixed inside the transition housing;

[0013] The first shaft of the radial internal combustion wave rotor is set in the first bearing seat through the first bearing, and the second shaft is set in the second bearing seat through the second bearing, so that the radial internal combustion wave rotor is located between the outer shell and the inner support frame and can rotate freely.

[0014] The intake ring is a hollow cylinder with open ends, fitted around the combustion ring. One end is sealed and fixedly connected to the first bearing seat, and the other end is sealed and fixedly connected to the transition shell. The intake ring has M rows of intake windows corresponding to the M rows of combustion channels. Each row of intake windows contains P circumferentially evenly arranged intake windows, and the angular interval between adjacent rows of intake windows is 360° / (M*P), where P is a natural number greater than or equal to 1. The intake ring also has several igniters corresponding to the intake windows. A sealing ring is provided between the intake ring and the outer wall of the combustion ring.

[0015] The exhaust ring is a hollow cylinder with open ends that mates with the inner wall of the combustion ring. One end is sealed and fixedly connected to the first bearing seat, and the other end is sealed and fixedly connected to the transition shell. The exhaust ring has M rows of exhaust windows that correspond one-to-one with the M rows of combustion channels. Each row of exhaust windows contains P circumferentially evenly arranged air intake windows, and the angular interval between adjacent rows of exhaust windows is 360° / (M*P). A sealing ring is provided between the exhaust ring and the inner wall of the combustion ring.

[0016] An air intake channel is formed between the outer shell, the outer wall of the outer support frame ring, the outer wall of the first bearing, and the air intake ring; an exhaust channel is formed between the inner support frame and the exhaust ring, the inner wall of the first bearing, the gradient part of the outer support frame, and the cylindrical part of the outer support frame.

[0017] The oil ring is disposed between the outer wall of the outer support frame ring and the outer shell, and is used for spraying oil.

[0018] As a further optimization of the radial internal combustion wave rotor turboshaft engine experimental device of the present invention, the outer wall of the first bearing is streamlined and the diameter gradually increases. On the one hand, this reduces the velocity of the incoming air before it flows through the oil ring, thereby reducing the total pressure loss. On the other hand, it increases the incoming velocity at the oil film atomization point, thereby enhancing the atomization effect.

[0019] As a further optimization of the radial internal combustion wave rotor turboshaft engine experimental device of the present invention, the outer support frame is hollow and has a number of ribs inside to strengthen its strength. The outer wall of its ring is provided with a number of evenly arranged flow holes in the circumferential direction for the flow of incoming air from the compressor. The end wall of its gradient part facing the air guide part and the end wall of its cylindrical part facing the air guide part are provided with a number of rows of evenly arranged cooling holes in the circumferential direction for forming an air film cooling the wall surface of the outer support frame.

[0020] Compared with the prior art, the present invention, employing the above technical solution, has the following technical effects:

[0021] Radial wave rotors have small axial dimensions and compact structures, which can make full use of the axial dimensions to generate higher output power. In addition, compared with traditional straight channels, the curved channels of the wave rotor can provide a longer combustion time, and more shock wave flame interactions can be generated within the curved channels, resulting in higher pressure gain. Attached Figure Description

[0022] Figure 1 This is a cross-sectional view of the present invention;

[0023] Figure 2 This is a schematic diagram of the radial internal combustion wave rotor in this invention;

[0024] Figure 3 This is a schematic diagram of the structure of the outer support frame in this invention;

[0025] Figure 4 This is a cross-sectional view of the outer support frame in this invention;

[0026] Figure 5 This is a cross-sectional view of the casing in this invention;

[0027] Figure 6 This is a schematic diagram of the intake ring structure in this invention;

[0028] Figure 7 This is a schematic diagram of the exhaust ring structure in this invention.

[0029] In the diagram, 1-radial internal combustion wave rotor, 2-outer support frame, 3-oil ring, 4-casing, 5-intake ring, 6-sealing ring between the intake ring and combustion ring, 7-exhaust ring, 8-sealing ring between the exhaust ring and combustion ring, 9-inner support frame, 10-first shaft, 11-combustion channel, 12-second shaft, 13-flow hole, 14-cooling hole, 15-outer wall of the first bearing, 16-rib plate, 17-outer shell, 18-transition shell, 19-inner shell, 20-intake window, 21-igniter, 22-exhaust window. Detailed Implementation

[0030] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings:

[0031] This invention can be implemented in many different forms and should not be considered limited to the embodiments described herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully express the scope of the invention to those skilled in the art. In the drawings, components are enlarged for clarity.

[0032] It should be understood that although the terms first, second, third, etc., may be used herein to describe various elements, components, and / or parts, these elements, components, and / or parts are not limited by these terms. These terms are merely used to distinguish elements, components, and / or parts from one another. Therefore, the first element, component, and / or part discussed below may be a second element, component, or part without departing from the teachings of this invention.

[0033] like Figure 1 As shown, the present invention discloses an experimental device for a radial internal combustion wave rotor turboshaft engine, including a radial internal combustion wave rotor, an outer support frame, an oil ring, a casing, an intake ring, an exhaust ring, an inner support frame, a first bearing, a second bearing, a first shaft seat, and a second shaft seat;

[0034] like Figure 2 As shown, the radial internal combustion wave rotor includes a first rotating shaft, a combustion ring, and a second rotating shaft. The first and second rotating shafts have the same structure, being hollow cylinders open at both ends. The combustion ring is also a hollow cylinder open at both ends, with its inner wall diameter smaller than that of the first rotating shaft and its outer wall diameter larger than that of the first rotating shaft. The outer wall of the combustion ring has M rows of equidistant combustion channels penetrating its inner wall, each row containing N circumferentially uniformly arranged combustion channels, where M is a natural number greater than or equal to 1 and N is a natural number greater than or equal to 2. The first rotating shaft, the combustion ring, and the second rotating shaft are coaxially fixed together in sequence.

[0035] like Figure 3 As shown, the outer support frame includes a ring, a transition section, and a cylindrical section. The ring is circular, and the cylindrical section is a hollow cylinder with openings at both ends. The diameter of the outer wall of the cylindrical section is smaller than the diameter of the inner wall of the ring, and the cylindrical section is located downstream of the ring. The outer side of the transition section is connected to the inner wall of the ring, and the inner side is connected to one upstream end of the cylindrical section, so that the ring and the cylindrical section form an arc transition.

[0036] like Figure 5 As shown, the casing includes an outer shell, a transition shell, and an inner shell. Both the outer shell and the inner shell are hollow cylinders with openings at both ends. The diameter of the inner wall of the outer shell is larger than the diameter of the outer wall of the inner shell. The outer side of the transition shell is sealed and coaxially fixed to the downstream end of the outer shell, and the inner side is sealed and coaxially fixed to the upstream end of the inner shell.

[0037] The inner support frame includes a fixing part and an air guiding part. The fixing part is a hollow cylinder with openings at both ends. Its outer wall diameter is equal to the inner wall diameter of the inner shell and it is coaxially fixed to the inner shell. The air guiding part is an annular ring with a U-shaped radial cross section. It is located upstream of the fixing part, and the outer end of the air guiding part is coaxially fixed to the upstream end of the fixing part, so that the opening of the air guiding part faces downstream.

[0038] The first bearing housing is fixed to the downstream end face of the outer support frame ring, and the second bearing housing is fixed inside the transition housing;

[0039] The first shaft of the radial internal combustion wave rotor is set in the first bearing seat through the first bearing, and the second shaft is set in the second bearing seat through the second bearing, so that the radial internal combustion wave rotor is located between the outer shell and the inner support frame and can rotate freely.

[0040] like Figure 1 , Figure 6 As shown, the intake ring is a hollow cylinder with open ends that fits around the combustion ring. One end is sealed and fixedly connected to the first bearing seat, and the other end is sealed and fixedly connected to the transition shell. The intake ring has M rows of intake windows that correspond one-to-one with the M rows of combustion channels. Each row of intake windows contains P circumferentially evenly arranged intake windows, and the angular interval between adjacent rows of intake windows is 360° / (M*P), where P is a natural number greater than or equal to 1. The intake ring also has several igniters that correspond one-to-one with the intake windows shown. A sealing ring is provided between the intake ring and the outer wall of the combustion ring.

[0041] like Figure 1 , Figure 7 As shown, the exhaust ring is a hollow cylinder with open ends that mates with the inner wall of the combustion ring. One end is sealed and fixedly connected to the first bearing seat, and the other end is sealed and fixedly connected to the transition shell. The exhaust ring has M rows of exhaust windows that correspond one-to-one with the M rows of combustion channels. Each row of exhaust windows contains P circumferentially evenly arranged intake windows, and the angular interval between adjacent rows of exhaust windows is 360° / (M*P). A sealing ring is provided between the exhaust ring and the inner wall of the combustion ring.

[0042] An air intake channel is formed between the outer shell, the outer wall of the outer support frame ring, the outer wall of the first bearing, and the air intake ring; an exhaust channel is formed between the inner support frame and the exhaust ring, the inner wall of the first bearing, the gradient part of the outer support frame, and the cylindrical part of the outer support frame.

[0043] The oil ring is disposed between the outer wall of the outer support frame ring and the outer shell, and is used for spraying oil.

[0044] like Figure 1 As shown, the outer wall of the first bearing is streamlined and the diameter gradually increases. On the one hand, this reduces the velocity of the incoming air before it passes through the oil ring, thus reducing the total pressure loss. On the other hand, it increases the incoming velocity at the oil film atomization point, thereby enhancing the atomization effect.

[0045] like Figure 4As shown, the outer support frame is hollow and has several ribs inside to strengthen it. The outer wall of its ring has several evenly arranged flow holes in the circumferential direction for the flow of incoming air from the compressor. Several rows of evenly arranged cooling holes in the circumferential direction are provided on the end wall of the transition section facing the air guide section and the end wall of the cylinder section facing the air guide section to form an air film cooling the wall surface of the outer support frame.

[0046] In this invention, the radial internal combustion wave rotor replaces the traditional combustion chamber structure. The pre-compressed air-fuel mixture undergoes isochoric combustion in the combustion channel, and the shape of the combustion channel can be freely changed to meet different needs.

[0047] Typically, in a radial wave rotor, air enters from the inside of the rotor's combustion chamber and exits from the outside. However, in this invention, to match the structure of a traditional turboshaft engine, the incoming air flows in from the outside of the rotor's combustion chamber, while the high-temperature combustion gas exits from the inside, thus driving the turbine. The airflow from the compressor mixes with fuel injected from the oil ring to form a premixed gas, which flows into each set of combustion channels through intake windows with different phase differences on the intake ring. An igniter is installed on the intake ring to ignite the mixture in the combustion channels for isochoric combustion. The high-temperature, high-pressure gas after combustion is discharged radially from the exhaust ring, and then flows axially through the curved flow channel of the curved pipe support, driving the turbine. This invention uses an isochoric combustion radial wave rotor instead of the isobaric combustion chamber of a traditional turboshaft engine, which can effectively improve the thermodynamic cycle efficiency and increase the output power.

[0048] It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. It should also be understood that terms such as those defined in general dictionaries should be understood to have the same meaning as in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless defined as herein.

[0049] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. An experimental apparatus for a radial internal combustion wave rotor turboshaft engine, characterized in that, It includes a radial internal combustion wave rotor, an outer support frame, an oil ring, a casing, an intake ring, an exhaust ring, an inner support frame, a first bearing, a second bearing, a first shaft seat, and a second shaft seat; The radial internal combustion wave rotor includes a first rotating shaft, a combustion ring, and a second rotating shaft. The first and second rotating shafts have the same structure, being hollow cylinders open at both ends. The combustion ring is also a hollow cylinder open at both ends, with its inner wall diameter smaller than that of the first rotating shaft and its outer wall diameter larger than that of the first rotating shaft. The outer wall of the combustion ring has M rows of equidistant combustion channels penetrating its inner wall, and each row of combustion channels contains N circumferentially uniformly arranged combustion channels, where M is a natural number greater than or equal to 1 and N is a natural number greater than or equal to 2. The first rotating shaft, the combustion ring, and the second rotating shaft are coaxially fixed together in sequence. The outer support frame includes a ring, a transition section, and a cylindrical section. The ring is circular, and the cylindrical section is a hollow cylinder with openings at both ends. The diameter of the outer wall of the cylindrical section is smaller than the diameter of the inner wall of the ring, and the cylindrical section is located downstream of the ring. The outer side of the transition section is connected to the inner wall of the ring, and the inner side is connected to one upstream end of the cylindrical section, so that the ring and the cylindrical section form an arc transition. The casing includes an outer shell, a transition shell, and an inner shell. Both the outer shell and the inner shell are hollow cylinders with openings at both ends. The diameter of the inner wall of the outer shell is larger than the diameter of the outer wall of the inner shell. The outer side of the transition shell is sealed and coaxially fixed to the downstream end of the outer shell, and the inner side is sealed and coaxially fixed to the upstream end of the inner shell. The inner support frame includes a fixing part and an air guiding part. The fixing part is a hollow cylinder with openings at both ends. Its outer wall diameter is equal to the inner wall diameter of the inner shell and it is coaxially fixed to the inner shell. The air guiding part is an annular ring with a U-shaped radial cross section. It is located upstream of the fixing part, and the outer end of the air guiding part is coaxially fixed to the upstream end of the fixing part, so that the opening of the air guiding part faces downstream. The first bearing housing is fixed to the downstream end face of the outer support frame ring, and the second bearing housing is fixed inside the transition housing; The first shaft of the radial internal combustion wave rotor is set in the first bearing seat through the first bearing, and the second shaft is set in the second bearing seat through the second bearing, so that the radial internal combustion wave rotor is located between the outer shell and the inner support frame and can rotate freely. The intake ring is a hollow cylinder with open ends, fitted around the combustion ring. One end is sealed and fixedly connected to the first bearing seat, and the other end is sealed and fixedly connected to the transition shell. The intake ring has M rows of intake windows corresponding to the M rows of combustion channels. Each row of intake windows contains P circumferentially evenly arranged intake windows, and the angular interval between adjacent rows of intake windows is 360° / (M*P), where P is a natural number greater than or equal to 1. The intake ring also has several igniters corresponding to the intake windows. A sealing ring is provided between the intake ring and the outer wall of the combustion ring. The exhaust ring is a hollow cylinder with open ends that mates with the inner wall of the combustion ring. One end is sealed and fixedly connected to the first bearing seat, and the other end is sealed and fixedly connected to the transition shell. The exhaust ring has M rows of exhaust windows that correspond one-to-one with the M rows of combustion channels. Each row of exhaust windows contains P circumferentially evenly arranged air intake windows, and the angular interval between adjacent rows of exhaust windows is 360° / (M*P). A sealing ring is provided between the exhaust ring and the inner wall of the combustion ring. An air intake channel is formed between the outer shell, the outer wall of the outer support frame ring, the outer wall of the first bearing, and the air intake ring; an exhaust channel is formed between the inner support frame and the exhaust ring, the inner wall of the first bearing, the gradient part of the outer support frame, and the cylindrical part of the outer support frame. The oil ring is disposed between the outer wall of the outer support frame ring and the outer shell, and is used for spraying oil.

2. The experimental apparatus for a radial internal combustion wave rotor turboshaft engine according to claim 1, characterized in that, The outer wall of the first bearing is streamlined, with the diameter gradually increasing. This reduces the velocity of the incoming air before it passes through the oil ring, thus reducing the total pressure loss. On the other hand, it increases the incoming velocity at the oil film atomization point, thereby enhancing the atomization effect.

3. The experimental apparatus for a radial internal combustion wave rotor turboshaft engine according to claim 1, characterized in that, The outer support frame is hollow and has several ribs inside to strengthen it. The outer wall of its ring has several evenly arranged flow holes in the circumferential direction for the flow of incoming air from the compressor. Several rows of evenly arranged cooling holes in the circumferential direction are provided on the end wall of the transition section facing the air guide section and the end wall of the cylinder section facing the air guide section to form an air film cooling the wall surface of the outer support frame.

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