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High-enthalpy propulsion wind tunnel air heating method and device

An air heating device and air heating technology are applied in the field of wind tunnel tests to achieve the effects of increasing total enthalpy, improving quality and reducing pollution levels

Active Publication Date: 2020-03-24
CHINA AERODYNAMICS RES & DEV CENT
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The main reason is that the airflow in the current combustion heater is a low-speed flow (Ma number is much smaller than 1), and the upper limit of heat release generated by combustion alone can only reach the total enthalpy corresponding to the flight Ma number 8

Method used

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  • High-enthalpy propulsion wind tunnel air heating method and device
  • High-enthalpy propulsion wind tunnel air heating method and device

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Experimental program
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Effect test

Embodiment 1

[0025] Embodiment 1: A kind of high enthalpy propulsion wind tunnel air heating method, such as figure 1 shown, including the following steps:

[0026] S1. Carry out primary heating, use the primary air heater 1 with an operating temperature of 1200-2800K to heat the pure air, and determine the heating working time according to the type of the selected primary air heater 1, the primary air heater 1 When the arc heating type is selected, the working time can reach several minutes. When a conventional scale heat storage heater is selected as the first-stage heater, the working time can reach several seconds. The first-stage heating makes the enthalpy increase Δh1 of the pure air flow greater than or equal to 1.6MJ / kg, the Ma number of the total enthalpy of the simulated air flow is 5-6.5, then oxygen is added, and the air flow is expanded to the state of Ma>2.0 by a supersonic nozzle;

[0027] S2. Carry out secondary heating, using a supersonic combustion heater to combust the...

Embodiment 2

[0039] Embodiment 2: A kind of high-enthalpy propulsion wind tunnel air heating device, such as figure 2 As shown, it includes a primary air heater 1 with an operating temperature of 1200-2800K, and a primary equipment nozzle 2 is connected to the outlet of the primary air heater 1 . A secondary air heater 3 is connected to the outlet end of the nozzle 2 of the primary equipment. The outlet end of the secondary air heater 3 is connected with a nozzle 4 of the secondary equipment. The outlet end of the nozzle 4 of the secondary equipment is connected with a test section 5 . The primary air heater 1 is any one of a resistance heater, a regenerative heater or an arc heater. The secondary air heater 3 is a supersonic combustion heater.

[0040] In this embodiment, the nozzle 2 of the first-stage equipment adopts a Laval nozzle, and the Mach number of the outlet of the nozzle is 1.5-3.0. It is determined according to the actual situation, and the corresponding outlet static tem...

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Abstract

The invention discloses a high-enthalpy propulsion wind tunnel air heating method and device, and relates to the technical field of wind tunnel tests, and the technical scheme is characterized in thatthe method comprises the following steps that S1, the first-stage heating is carried out: a first-stage air heater is used to heat pure air; and S2, secondary heating is conducted, specifically, a supersonic combustion heater is adopted to organize combustion of the air flow passing through the S1 to conduct secondary heating, then combustion heating is conducted by supplementing oxygen and hydrogen into the supersonic combustion heater, and total enthalpy simulation of the flight mach number 12 is achieved. The device comprises the first-stage air heater, a first-stage equipment spray pipe,a second-stage air heater, a second-stage equipment spray pipe and a test section. Compared with a shock tunnel, the time of a ground test with the flight Mach number of 8-12 can be prolonged by one to two orders of magnitudes, the equipment construction and operation cost is remarkably reduced, the method can be applied to simulating flight conditions with the Mach number of 8 or below, the pollution degree in the simulation test process is reduced, and the quality of simulated incoming flow is improved.

Description

technical field [0001] The invention relates to the technical field of wind tunnel tests, more specifically, it relates to a method and device for heating air in a high-enthalpy propulsion wind tunnel. Background technique [0002] The high Mach number scramjet engine is the ideal power demand for global arrival in the next 1-2 hours, intercontinental real-time strike weapons and low-cost orbital missions. It plays an important role in enhancing my country's high-speed and long-range penetration capabilities and supporting national defense and military construction in the new era. Practical significance. So far, shock wave reflection wind tunnels and arc heating wind tunnels are more feasible to simulate aerodynamic propulsion test equipment with higher Mach number (Ma>7). The test time of the shock wave reflection wind tunnel is limited to a few to tens of milliseconds, and the test time is significantly reduced as the simulated Ma number increases. The arc heating wind...

Claims

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Application Information

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IPC IPC(8): G01M9/04
CPCG01M9/04Y02E20/34
Inventor 邢建文邓维鑫何粲杨顺华向周正欧阳浩张弯洲蒋劲张磊赵国柱肖保国郑帅胡俊逸罗征
Owner CHINA AERODYNAMICS RES & DEV CENT