Variable cross-section shock wave induced ultralow-pressure self-ignition experimental device and method

An experimental device and self-ignition technology, which is applied in the direction of measuring devices, instruments, gas turbine engine testing, etc., can solve the problem that the high-voltage driving section and the low-pressure experimental section cannot be stably blocked, so as to achieve both experimental reliability, strong dependence, and improvement Effect of Driving Gas Pressure

Pending Publication Date: 2021-10-01
XI AN JIAOTONG UNIV
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Problems solved by technology

[0004] In order to solve the problem of accurate characterization of self-ignition in the ultra-low pressure environment of near-space aircraft, the present invention proposes an experimental device and method for ultra-low pressure self-ignition induced by variable-section shock waves. This method can not only match the high-inten

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  • Variable cross-section shock wave induced ultralow-pressure self-ignition experimental device and method
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Embodiment Construction

[0013] The present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments.

[0014] see figure 2 The embodiments of the present invention are described to make the content of technical methods clearer and easier to understand. A variable cross-section shock wave-induced ultra-low pressure self-ignition experimental device and method described in this embodiment includes: a high-pressure driving section 1, a dual-mode membrane rupture mechanism 2, a conical transition section 3, a low-pressure experimental section 4, and a first pressure Sensor 5, second pressure sensor 6, signal converter 7, data collector 8, gas mixing tank 9, vacuum pump group 10, strong driving gas 11, sewing driving gas 12, and common rail pipeline 13.

[0015] A variable cross-section shock wave induced ultra-low pressure self-ignition experiment device and method of the present invention utilizes a weldless high-strength flange to conn...

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Abstract

The invention discloses a variable cross-section shock wave induced ultralow-pressure self-ignition experimental device and method. The variable cross-section shock wave induced ultralow-pressure self-ignition experimental device comprises a high-pressure driving section, a dual-mode membrane breaking mechanism, a conical transition section and a low-pressure experimental section which are coaxially connected in sequence, wherein the high-pressure driving section is coaxially connected with the dual-mode membrane breaking mechanism; the high-pressure driving section and the double-membrane breaking mechanism are separated by a membrane; the double-membrane breaking mechanism is coaxially connected with a small-diameter port of the conical transition section, and the double-membrane breaking mechanism and the conical transition section are blocked by a membrane; the large-diameter port of the conical transition section is coaxially connected with the low-pressure experiment section, high-strength shock waves generated by a traditional shock tube can be matched, the defect that the traditional shock tube cannot stably block the high-pressure driving section and the low-pressure experiment section can be overcome, and accurate measurement of ultralow-pressure self-ignition delay of the near-space aircraft is effectively obtained.

Description

technical field [0001] The invention belongs to the technical field of ignition and combustion of near-space vehicles, and relates to an ultra-low pressure self-ignition experimental device and method induced by a variable-section shock wave. Background technique [0002] Near space has many flight advantages in both aviation space and outer space, and it is a must for future space combat strategists. The self-ignition delay characteristic is the key to the design of mainstream aircraft in near space, such as scramjet engine and turbine combined engine, and its accurate experimental characterization is directly related to the combustion stability and operational reliability of near space aircraft. [0003] The high-altitude atmosphere is thin, and the air density at conventional flight altitudes (32km) is only one percent of that on the ground. The air intake pressure during flight is extremely low, making accurate measurement of self-ignition difficult. The traditional sho...

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Application Information

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IPC IPC(8): G01M15/14G01M15/02
CPCG01M15/14G01M15/02
Inventor 张英佳孙五川黄文林黄佐华
Owner XI AN JIAOTONG UNIV
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