发明名称 |
ИНТЕГРАЛЬНЫЙ РАКЕТНО-ПРЯМОТОЧНЫЙ ДВИГАТЕЛЬ (ИРПДТ) |
摘要 |
FIELD: engines and pumps. ^ SUBSTANCE: integral rocket ramjet engine consists of gas generator with a hard fuel charge, combustion chamber equipped with at least one branch, non-removable cover, arranged on the branch; the said cover has a case with a grid composed of longitudinal and transverse ribs, and a plate of a laminated structure. The grid is of full strength with a wall of the combustion chamber and projects into the combustion chamber at a thickness of a heat shielding coating of the latter. The plate consists of metal foil and protecting adhering layer. A heat shielding coating is applied on an inside surface of the combustion chamber; while a protecting adhering layer is applied on the surface of the said coating. ^ EFFECT: increased reliability of an integral rocket ramjet engine at the transitive stage from a start to cruise mode; upgraded conditions of air flow supply into a combustion chamber and increased ratio of recovery of a combustion chamber full pressure during engine operation. ^ 3 cl, 9 dwg |
申请公布号 |
RU2006122264(A) |
申请公布日期 |
2008.01.10 |
申请号 |
RU20060122264 |
申请日期 |
2006.06.22 |
申请人 |
Федеральное государственное унитарное предпри тие"Центральный институт авиационного моторостроени имени П.И. Баранова" (RU);Открытое акционерное общество "Машиностроительноеконструкторское бюро "Искра" им. И.И. Картукова" (RU) |
发明人 |
Верхоломов В чеслав Кириллович (RU);Суриков Евгений Валентинович (RU);Яновский Леонид Самойлович (RU);Граменицкий Михаил Дмитриевич (RU);Животов Николай Павлович (RU);Рыбаулин Сергей Николаевич (RU) |
分类号 |
F02K7/00 |
主分类号 |
F02K7/00 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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