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CN-121993316-A - Pulse detonation turbine engine

CN121993316ACN 121993316 ACN121993316 ACN 121993316ACN-121993316-A

Abstract

The invention relates to the technical field of aeroengines, and discloses a pulse detonation turbine engine, which comprises an air inlet assembly, a supercharging assembly, a combustion chamber casing, a pulse detonation combustion chamber, a nozzle assembly, a transition assembly and an exhaust assembly, wherein the air inlet assembly is connected with the supercharging assembly; the pulse detonation combustion chamber is provided with a first channel and a second channel at the first end, a first exhaust channel is arranged at the second end and extends outwards from the combustion chamber casing, two channels are formed between the combustion chamber casing and the pulse detonation combustion chamber and are communicated with the first channel, the transition component is arranged at one end, close to the exhaust direction, of the supercharging component, and the transition component is communicated with the second channel. The invention can effectively weaken the strength of returning knocking by forming two channels between the pulse knocking combustion chamber and the combustion chamber casing and utilizing the cavity effect of the two channels, thereby reducing the back transfer pressure faced by the pressurizing assembly, and simultaneously, the air can cool the wall surface of the pulse knocking combustion chamber after entering the two channels from the pressurizing assembly.

Inventors

  • PENG CHANGXIN
  • GUO QINGLIN
  • YING WEI
  • WANG QIDAO
  • HUANG JUNJIE

Assignees

  • 中国航发湖南动力机械研究所

Dates

Publication Date
20260508
Application Date
20260310

Claims (10)

  1. 1. A pulse detonation turbine engine, comprising: An air intake assembly (10); A supercharging assembly (20), wherein one end of the supercharging assembly (20) is connected and communicated with the air inlet assembly (10); a combustion chamber casing (30), wherein the combustion chamber casing (30) is connected with the other end of the supercharging assembly (20); A pulse detonation combustor (40) having a first end and a second end along an engine axis, the first end having a first passage (43) and a second passage (44), the second end having a first exhaust passage (45) and extending outwardly from the combustor casing (30), the combustor casing (30) and the pulse detonation combustor (40) forming two passages therebetween, the two passages being in communication with the first passage (43); -a nozzle assembly (50), said nozzle assembly (50) extending through said combustion chamber casing (30), said nozzle assembly (50) having an orifice disposed within said pulse detonation combustion chamber (40), said nozzle assembly (50) being adapted to inject fuel and fire into said pulse detonation combustion chamber (40); The transition assembly (60) is arranged at one end, close to the exhaust direction, of the supercharging assembly (20) along the axial direction of the engine, the transition assembly (60) is communicated with the second channel (44), and the transition assembly (60) is in transmission connection with the supercharging assembly (20); An exhaust assembly (70), the exhaust assembly (70) comprising an exhaust casing (71), the exhaust casing (71) being connected with the combustion chamber casing (30), the exhaust casing (71) having an exhaust port (711), the exhaust port (711) being in communication with the first exhaust passage (45), the exhaust port (711) being in communication with the transition assembly (60).
  2. 2. The pulse detonation turbine engine of claim 1, wherein the pulse detonation combustor (40) comprises a flow guiding structure (41) and a detonation combustion structure (42), the detonation combustion structure (42) is connected with the flow guiding structure (41), one end of the detonation combustion structure (42) away from the flow guiding structure (41) is provided with the first exhaust channel (45), one end of the detonation combustion structure (42) close to the flow guiding structure (41) is provided with the first channel (43), the first channel (43) is a rotational flow air inlet channel, the second channel (44) is formed in the flow guiding structure (41), and the spray hole is arranged in the detonation combustion structure (42).
  3. 3. The pulse detonation turbine engine of claim 2, wherein the combustor casing (30) comprises a combustion chamber casing (31) and a combustion chamber casing (32), the combustion chamber casing (32) being connected with the supercharging assembly (20) and the detonation combustion structure (42), respectively, the combustion chamber casing (31) being connected with the detonation combustion structure (42), respectively, the flow guiding structure (41) being disposed through the combustion chamber casing (31).
  4. 4. A pulse detonation turbine engine as claimed in any one of claims 1-3, characterised in that said supercharging assembly (20) comprises a compressor (21) and a compressor casing (22), both ends of said compressor casing (22) being connected to said intake assembly (10) and said combustion chamber casing (30) respectively, said compressor (21) being arranged in said compressor casing (22), an inlet of said compressor (21) being in communication with said intake assembly (10), an outlet of said compressor (21) being in communication with said two-way passage, said compressor (21) being in driving connection with said transition assembly (60).
  5. 5. The pulse detonation turbine engine of claim 4, wherein the transition assembly (60) includes a transition casing (61), a centripetal turbine (62) and a turbine casing (63), the centripetal turbine (62) is disposed within the turbine casing (63), the turbine casing (63) is connected with the pulse detonation combustion chamber (40), the turbine casing (63) is connected with the transition casing (61), the transition casing (61) is connected with the combustion chamber casing (30), the centripetal turbine (62) is in communication with the second channel (44), the centripetal turbine (62) is in driving connection with the compressor (21), a transition channel is formed within the transition casing (61), and the transition channel is in communication with the exhaust assembly (70).
  6. 6. The pulse detonation turbine engine of claim 5, wherein the transition casing (61) includes a transition inner casing (611) and a transition outer casing (612), the transition inner casing (611) and the transition outer casing (612) are disposed at intervals to form the transition channel, the transition outer casing (612) is connected with the turbine casing (63), the transition outer casing (612) is connected with the combustor casing (30), the transition assembly (60) further includes a first support plate (81) and a second support plate (82), the first support plate (81) is disposed between the transition inner casing (611) and the transition outer casing (612), and the second support plate (82) is disposed between the transition outer casing (612) and the combustor casing (30).
  7. 7. The pulse detonation turbine engine of claim 6, wherein the exhaust assembly (70) further comprises an exhaust cone (72), the exhaust cone (72) being connected to the transition inner casing (611), a second exhaust passage (84) being formed between the exhaust cone (72) and the transition outer casing (612), the second exhaust passage (84) being in communication with the exhaust port (711).
  8. 8. The pulse detonation turbine engine of claim 7, wherein the exhaust assembly (70) further comprises a lobe mixer (73), the lobe mixer (73) being disposed at an end of the transition casing (61) proximate to the exhaust port (711), the lobe mixer (73) having a first guide surface (731) and a second guide surface (732), the first guide surface (731) being adapted to direct the flow of the first exhaust channel (45), the second guide surface (732) being adapted to direct the flow of the second exhaust channel (84).
  9. 9. A pulse detonation turbine engine as claimed in any one of claims 1-3, characterised in that said air intake assembly (10) comprises an air intake casing (11) and an air intake cone (12), said air intake casing (11) being connected to said supercharging assembly (20), said air intake cone (12) being arranged in said air intake casing (11), said air intake cone (12) being arranged at an end of said supercharging assembly (20) remote from said transition assembly (60).
  10. 10. A pulse detonation turbine engine as claimed in any one of claims 1-3, characterised in that said nozzle assembly (50) comprises a fuel nozzle (51) and an ignition nozzle (52), said fuel nozzle (51) and said ignition nozzle (52) both extending through said combustion chamber casing (30) and into said pulse detonation combustion chamber (40), said ignition nozzle (52) being arranged on a side of said fuel nozzle (51) adjacent to said exhaust assembly (70).

Description

Pulse detonation turbine engine Technical Field The invention relates to the technical field of aeroengines, in particular to a pulse detonation turbine engine. Background The combustion mode of a traditional aeroengine combustion chamber can be similar to isobaric combustion, and the pressure difference between the inlet and the outlet of the combustion chamber is small. Unlike conventional combustion modes, pulse detonation combustion is a type of boost combustion in which the combustion process approximates to constant volume combustion, and the working medium obtains a pressure gain after passing through the pulse detonation combustion chamber, with the outlet pressure of the chamber being greater than the inlet pressure of the chamber. Turbine engines based on pulse detonation combustion have higher cycle thermal efficiency and power capability than conventional isobaric combustion based turbine engines under the same engine inlet parameters. Pulse detonation turbine engines, while theoretically having significant advantages, have some problems in their engineering applications. The detonation chamber also forms an upstream propagating "return detonation wave" when forming a downstream propagating detonation wave, which, although less intense than the detonation wave, still significantly affects the operation of the upstream compressor and thus the engine performance. Disclosure of Invention The invention provides a pulse detonation turbine engine, which aims to solve the working problem of an upstream compressor affected by return detonation waves. The invention provides a pulse detonation turbine engine, which comprises an air inlet component, a supercharging component, a combustion chamber casing, a pulse detonation combustion chamber, a nozzle component, a transition component and an exhaust component, wherein one end of the supercharging component is connected and communicated with the air inlet component, the combustion chamber casing is connected with the other end of the supercharging component, the pulse detonation combustion chamber is provided with a first end and a second end along the axial direction of the engine, the first end is provided with a first channel and a second channel, the second end is provided with a first exhaust channel and extends outwards from the combustion chamber casing, a two-way channel is formed between the combustion chamber casing and the pulse detonation combustion chamber, the two-way channel is communicated with the first channel, the nozzle component penetrates through the combustion chamber casing, the nozzle component is provided with spray holes, the spray holes are arranged in the pulse detonation combustion chamber, the nozzle component is suitable for spraying fuel and igniting in the pulse detonation combustion chamber, the transition component is arranged at one end, close to the exhaust direction of the supercharging component, of the transition component is communicated with the second channel, the transition component is communicated with the exhaust channel, the exhaust channel is communicated with the exhaust channel, and the exhaust channel is communicated with the exhaust channel. The pulse detonation combustor has the beneficial effects that the two channels are formed between the pulse detonation combustor and the combustor casing, the strength of returning detonation can be effectively weakened by utilizing the cavity effect of the two channels, so that the counter-transfer pressure facing the supercharging assembly is reduced, and meanwhile, after air enters the two channels from the supercharging assembly, the wall surface of the pulse detonation combustor can be cooled. In an alternative embodiment, the pulse detonation combustion chamber includes a flow guiding structure and a detonation combustion structure, the detonation combustion structure is connected with the flow guiding structure, one end of the detonation combustion structure away from the flow guiding structure is provided with the first exhaust channel, one end of the detonation combustion structure close to the flow guiding structure is provided with the first channel, the first channel is a rotational flow air inlet channel, the second channel is formed in the flow guiding structure, and the spray hole is arranged in the detonation combustion structure. The cyclone type detonation combustor has the advantages that pre-rotation is generated during air intake through the cyclone air intake channel, mixing of fuel and air is enhanced, the conversion distance from detonation to detonation is further reduced, the length of the detonation chamber in the flow direction is reduced, the working frequency of the detonation chamber is improved, meanwhile, the strength of returning detonation waves entering the two channels is further reduced, and the diversion structure introduces part of returning detonation waves into the transition assembly and pushes the turbine to do work so as