Designing a turbomachine of environmental control system for missile-carrier aircraft of air launch systems
Abstract
Recently, there has been growing interest in outer-space rocket launch systems with a renewable first stage. One of the promising options for such a scheme is an air launch system when a rocket rises into the stratosphere by the aircraft. At the same time, the aircraft needs an environmental control system for the cockpit and auxiliary environmental controlled compartments. To increase the payload of an aircraft, it is interesting to consider options for an environmental control system (ECS) without air sampling from aircraft engines. In this case, the option of using vapor compression cooling is interesting, and in this situation, the ECS turbo compressor does not need to increase the air pressure up to several atmospheres - but only to a value of about one atmosphere. In this paper, we consider a progressive method for designing a turbo compressor impeller. In using the proposed ECS scheme, the energy consumption for the needs of the environmental control system is reduced when parking in summer on the ground by 10 times, in cruise flight by 16.6 times. As a result of comparing the calculations of the turbo generator, performed according to the classical methodology and performed during modeling, it was revealed that using the same initial data, different impeller geometry is obtained. This may be due to the fact that the simulation takes into account the reality of the properties of the working gas and more accurately takes into account the internal leakage of gas from the region of high pressure to low.
- Publication:
-
XLIII Academic Space Conference: dedicated to the memory of academician S.P. Korolev and other outstanding Russian scientists - Pioneers of space exploration
- Pub Date:
- November 2019
- DOI:
- 10.1063/1.5133178
- Bibcode:
- 2019AIPC.2171c0012Z