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Analysis of low-thrust liquid rocket engines with a methane air pump unit
- Authors: Ivanov A.I.1, Kositsin I.P.1, Borisov V.A.2
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Affiliations:
- «Kuznetsov» public company, Samara
- Samara National Research University
- Issue: Vol 15, No 4 (2016)
- Pages: 75-80
- Section: AIRCRAFT AND SPACE ROCKET ENGINEERING
- URL: https://journals.ssau.ru/vestnik/article/view/3307
- DOI: https://doi.org/10.18287/2541-7533-2016-15-4-75-80
- ID: 3307
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Abstract
The first airplane working on cryogenic fuel was developed in the USSR in early 1980s on the basis of the passenger aircraft Tu-154. It was then modified using a hydrogen engine installed instead of one of the three kerosene engines. That bypass turbo-jet engine was developed in Russia (Samara) under the guidance of General Designer academician N.D. Kuznetsov. The engine working on liquid hydrogen was designated NK-88 and the one working on liquid methane – NK-89. A unique hydrogen turbopump unit was created for the supply of cryogenic fuel. The unit can also be used for liquid methane due to the possibility of readjusting the rotor frequency. To minimize the financial expenditures it is proposed to use the turbo-pump in low-thrust rocket engines that use liquid methane as fuel.
About the authors
A. I. Ivanov
«Kuznetsov» public company, Samara
Author for correspondence.
Email: alex_slavross@mail.ru
Head of Department of Rocket Engines and Cryoengineering
Russian FederationI. P. Kositsin
«Kuznetsov» public company, Samara
Email: alex_slavross@mail.ru
Candidate of Science (Engineering)
Lead engineer of the Department of Rocket Engines and Cryoengineering
V. A. Borisov
Samara National Research University
Email: valery.boris2013@yandex.ru
Candidate of Science (Engineering)
Associate Professor
Russian FederationReferences
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