Rotating sliding arc plasma combustion-supporting exciter in aeroengine combustor

Abstract

The utility model relates to a rotary sliding arc plasma combustion-supporting exciter of an aeroengine combustion chamber, and an axial flow swirler is located in the middle section of the anode casing. The cathode cone electrode is located below the axial flow cyclone; the lower end of the cathode electrode rod passes through the central hole of the axial flow cyclone and is fitted into the central blind hole on the upper end surface of the cathode cone electrode. The upper end of the cathode electrode rod is loaded into the center hole of the electrode installation isolation seat. The electrode installation isolation seat is fixedly installed in the inner hole of the anode casing and installed at the end of the large diameter section of the anode casing. An air inlet nozzle sealingly connected with the engine air supply device is installed on the outer peripheral surface of the large diameter section of the anode casing. The invention improves the combustion efficiency of the combustion chamber of the aero-engine, improves the uniformity of the outlet of the combustion chamber and widens the stable combustion range of the combustion chamber, and overcomes the problem that the existing plasma combustion-supporting technology is not suitable for use in the high-temperature and high-pressure environment of the combustion chamber of the aero-engine Insufficient, it has the characteristics of producing a large number of active particles, small size, simple structure and strong versatility.

Description

Technical field [0001] The invention relates to a plasma combustion intensification technology in the field of aerodynamics, in particular to a rotary sliding arc plasma combustion-supporting exciter for an aeroengine combustion chamber. Background technique [0002] As the performance of fighter jets continues to improve, higher requirements are placed on the performance of aero engines. The US Department of Defense proposed the "Comprehensive High-Performance Turbine Engine Technology Plan" with the goal of doubling the thrust-to-weight ratio of aero engines by the beginning of the 21st century. , That is, 15-20. One of the most effective ways to increase the thrust-to-weight ratio is to increase the unit thrust of the engine. The effective way to increase the unit thrust is to increase the temperature at the outlet of the combustion chamber, that is, the gas temperature in front of the turbine. On the other hand, advanced aero engines should also have higher reliability. For...

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Problems solved by technology

[0006] In order to overcome the disadvantages of complex structure and large size in the prior art, which cannot adapt to the harsh working environment of the aero-engine combustor, the present invention proposes a rotary sliding arc plasma combustion-supporting actuator for the aero-engine combustor

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