Method and device for measuring supercritical and gaseous hydrocarbon fuel dense flow

A hydrocarbon fuel, supercritical technology, applied in the field of aerospace measurement, can solve the problems of high cost, high measurement cost, low efficiency, etc., and achieve the effect of reducing requirements, reducing experimental difficulty, and high measurement efficiency

Active Publication Date: 2014-08-06
NAT UNIV OF DEFENSE TECH
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

Using this method at the same time, only one state point (referring to temperature and pressure) can be obtained at a time under the dense flow, the efficiency is low, and the measurement cost is high
It can be seen that this method has low efficiency and high cost

Method used

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  • Method and device for measuring supercritical and gaseous hydrocarbon fuel dense flow
  • Method and device for measuring supercritical and gaseous hydrocarbon fuel dense flow
  • Method and device for measuring supercritical and gaseous hydrocarbon fuel dense flow

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Embodiment Construction

[0032] The present invention will be described in detail below in conjunction with the accompanying drawings.

[0033] The invention measures the density of supercritical and gaseous hydrocarbon fuels in different states by designing the throttling throat area of ​​each sonic nozzle so that the fuel reaches the speed of sound at each throttling throat, that is, reaches the "choked" state. flow.

[0034] When the fuel to be tested flows stably in the device of the present invention, the mass flow rate of the fuel passing through each throttling throat is the same. From the known tight flow of the fuel to be tested at low pressure (P between 0.5-2.0Mpa), calculate the tight flow of the fuel to be tested at the second throat, and then pass according to the formula Calculate the dense flow of the first throat, that is, the dense flow of the fuel to be measured at the inlet of the first sonic nozzle. in are the dense flow through the sonic nozzle 1 and the sonic nozzle 2 respe...

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Abstract

The invention discloses a device for measuring supercritical and gaseous hydrocarbon fuel dense flow. The device comprises more than two sonic nozzles in serial connection, and each nozzle comprises an isometric straight section, a shrinkage section, a throttling throat portion and an expansion section; the isometric straight section of the first sonic nozzle is connected with an outlet of a hydrocarbon fuel heating device; each sonic nozzle reaches the sonic speed at the corresponding throat portion. The measuring method includes the steps: firstly, heating a to-be-measured fuel to a temperature about To and feeding the heated to-be-measured fuel; secondly, measuring an inlet pressure intensity P'm and a temperature T'm of the isometric straight section of a sonic nozzle m; thirdly, calculating a dense flow value of the to-be-measured fuel under the inlet pressure intensity P'm and the temperature T'm of the isometric straight section of the sonic nozzle m according to an equation: Mm=m / Am, wherein Am refers to the throat area of the sonic nozzle m. Using the device and the method can accurately measure the dense flow of the supercritical and gaseous hydrocarbon fuel reaching a 'choked' state under different state points with low cost.

Description

technical field [0001] The invention belongs to the field of aerospace measurement, and in particular relates to a fuel system mass flow measurement device and method. Background technique [0002] In order to ensure the structural reliability of the aircraft during long-term operation, scramjet engines and aero-engines need to cool the aircraft. The regenerative cooling method first uses the fuel as a coolant, and then injects the fuel after absorbing heat into the combustion to participate in the combustion. Under the condition of Ma<8, endothermic hydrocarbon fuel is a hypersonic vehicle fuel with excellent comprehensive performance. The heat absorption of endothermic hydrocarbon fuel changes with different flight conditions, and its state also changes continuously during the process. When the fuel temperature and pressure are higher than its thermodynamic critical temperature and critical pressure, respectively, the fuel enters the supercritical state; under a certa...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01F1/86
Inventor 钟战王振国孙明波雷静梁剑寒李清廉
Owner NAT UNIV OF DEFENSE TECH
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