Studying parameters of aircraft cryogenic turbo-pump unit by the aircraft flight cycle

Aeronautical and Space-Rocket Engineering

Thermal engines, electric propulsion and power plants for flying vehicles


Аuthors

Aslanov A. R.*, Raznoschikov V. V.**, Stol’nikov A. M.***

Central Institute of Aviation Motors named after P.I. Baranov, CIAM, 2, Aviamotornaya str., Moscow, 111116, Russia

*e-mail: asvar.aslanov96@mail.ru
**e-mail: raznoschikov@ciam.ru
***e-mail: R8314459848@gmail.com

Abstract

According to the forecasts of the International Energy Agency, by the year 2040 the demand for liquefied natural gas (LNG) in the European Union will increase four times and twice in China. The LNG can become a greener substitute for oil and coal in the fast-growing urban areas of the developing world.

The Soviet Union was the first in the world to test a liquid hydrogen airplane in 1988, and in 1989 began equipment testing and research into the cryo-aircraft possibilities with the LNG utilization. Subsequently, several LNG-powered aircraft projects were developed, but they could not be realized for objective reasons.

One of the main problems of creating aviation cryogenic fuel system is the development of aviation cryogenic turbo-pump unit (TPU) capable of operating in the range of fuel consumption larger than the TPU for the space-rocket technology.

The article presents simulation of the aircraft turbo pump unit modelling, with account for the joint operation with the other units of the cryogenic fuel system.

Two TPU structures are possible in the aviation cryogenic system: the so-called “open scheme” and closed scheme. In the close scheme the pump driving is realized by the turbine, which working body is a cryogenic fuel warmed in the heat exchange unit. The pump driving in the open scheme is brought about from the external power source, i.e. electric motor. The closed scheme is more energy efficient, though it requires joint operation of the fuel system aggregates. The open scheme was selected as the object of research.

A mathematical model of the TPU, which has two modes of operation, has been developed for conducting computational and theoretical studies. The rated mode allows defining the TPU geometrical sizes. The non-rated mode allows defining the TPU basic parameters and plotting consumption-head-flow characteristic based on geometrical sizes, mass fuel consumption and input pressure. It should be noted that the TPU mathematical model operates in aggregate with mathematical model of the cryogenic fuel tank.

As the result of the calculation, the required power, pressure at the TPU outlet, as well as the flow and pressure characteristics of the pump are being determined by the aircraft flight cycle.

Keywords:

cryogenic pump, cryogenic fuel system, liquefied natural gas pump, cryogenic fuel aircraft engine, aircraft turbo-pump unit

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