Email this article Influence of combustion chamber geometry and compression ratio on the main parameters of a diesel aircraft engine
- Authors: Gureev V.M.1, Khairullin A.K.1, Varlamov F.A.1, Gumerov I.F.2, Khafizov R.K.2
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Affiliations:
- Tupolev Kazan National Research Technical University
- OAO KAMAZ
- Issue: Vol 60, No 2 (2017)
- Pages: 219-222
- Section: Aircraft and Rocket Engine Design and Development
- URL: https://journal-vniispk.ru/1068-7998/article/view/230084
- DOI: https://doi.org/10.3103/S106879981702009X
- ID: 230084
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Abstract
This paper considers the problem of increasing the fuel efficiency of a diesel aircraft engine and decreasing the smokiness of its exhaust gases (EG) by means of the experimental determination of optimum compression ratio and combustion chamber dimensions. Necessity for matching of these parameters in a wide variation range of load and crankshaft speed was identified and proved.
About the authors
V. M. Gureev
Tupolev Kazan National Research Technical University
Email: info@pleiadesonline.com
Russian Federation, ul. Karla Marksa 10, Kazan, 420111 Tatarstan
A. Kh. Khairullin
Tupolev Kazan National Research Technical University
Email: info@pleiadesonline.com
Russian Federation, ul. Karla Marksa 10, Kazan, 420111 Tatarstan
F. A. Varlamov
Tupolev Kazan National Research Technical University
Email: info@pleiadesonline.com
Russian Federation, ul. Karla Marksa 10, Kazan, 420111 Tatarstan
I. F. Gumerov
OAO KAMAZ
Email: info@pleiadesonline.com
Russian Federation, pr. Avtozavodskii 2, Naberezhnye Chelny, 423827 Tatarstan
R. Kh. Khafizov
OAO KAMAZ
Email: info@pleiadesonline.com
Russian Federation, pr. Avtozavodskii 2, Naberezhnye Chelny, 423827 Tatarstan
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