Flow parameters at the supersonic combustor entrance at tests in quasistationary impulse regime

S. A. Akinin, M. A. Goldfeld, A. V. Starov

Результат исследования: Публикации в книгах, отчётах, сборниках, трудах конференцийстатья в сборнике материалов конференциинаучнаярецензирование

Аннотация

The results of the flow investigation at the supersonic combustor entrance at tests in the regime of an attached pipe-line are presented. As a source of working gas, a discharge pre-chamber of an impulse wind tunnel was used. The three-dimensional numerical simulation was performed using the software package ANSYS Fluent from the nozzle critical section to the combustor entrance with experimental initial data. The experiments were carried out with the following airflow parameters: M = 4, total pressure P0 = 5.7÷2.0 MPa and total temperature T0=1750÷1200 K. Air flow characteristics and their distribution at the combustor entrance were obtained. It is established that the Mach number field non-uniformity in the flow core at the combustor entrance is 2.3% with a maximum thickness of the boundary layer of 10.7 mm. A good agreement between the calculated and experimental data was obtained.

Язык оригиналаанглийский
Название основной публикации19th International Conference on the Methods of Aerophysical Research, ICMAR 2018
Редакторы Fomin
ИздательAmerican Institute of Physics Inc.
Число страниц5
Том2027
ISBN (электронное издание)9780735417472
DOI
СостояниеОпубликовано - 2 ноя 2018
Событие19th International Conference on the Methods of Aerophysical Research, ICMAR 2018 - Akademgorodok, Novosibirsk, Российская Федерация
Продолжительность: 13 авг 201819 авг 2018

Серия публикаций

НазваниеAIP Conference Proceedings
ИздательAMER INST PHYSICS
Том2027
ISSN (печатное издание)0094-243X

Конференция

Конференция19th International Conference on the Methods of Aerophysical Research, ICMAR 2018
СтранаРоссийская Федерация
ГородAkademgorodok, Novosibirsk
Период13.08.201819.08.2018

Fingerprint Подробные сведения о темах исследования «Flow parameters at the supersonic combustor entrance at tests in quasistationary impulse regime». Вместе они формируют уникальный семантический отпечаток (fingerprint).

Цитировать