FIELD: rocket engineering.
SUBSTANCE: proposed structural member 1 has shell forming inner space to pass gas and it is formed by at least first part 5 consisting of inner wall 8, outer wall 9 and at least one cooling channel 11 between walls. End 12 of inner wall of first part of member is connected with second part 6 of member. Place 18 of connection is located at a distance from inner of member. Invention contains description of method of manufacture of such member.
EFFECT: increased service life of structural members, and provision of economic and effective method of manufacture of components of jet engine.
33 cl, 15 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| ROCKET ENGINE MEMBER AND METHOD OF ITS MANUFACTURE | 2002 |
|
RU2274763C2 |
| METHOD OF MANUFACTURE OF ROCKET ENGINE EXHAUST NOZZLE | 2002 |
|
RU2274762C2 |
| ROCKET ENGINE MEMBER AND METHOD OF ITS MANUFACTURE | 2002 |
|
RU2278292C2 |
| COMPONENT OF ROCKET ENGINE AND METHOD FOR MANUFACTURE OF ROCKET ENGINE COMPONENT | 2002 |
|
RU2273756C2 |
| COOLING SYSTEM OF LIQUID-PROPELLANT ENGINE COMBUSTION CHAMBER | 2013 |
|
RU2511982C1 |
| COOLING SYSTEM OF LIQUID-PROPELLANT ENGINE COMBUSTION CHAMBER | 2013 |
|
RU2511791C1 |
| LIQUID-PROPELLANT ROCKET ENGINE COMBUSTION CHAMBER COOLING SYSTEM | 2013 |
|
RU2514863C1 |
| COOLING SYSTEM OF LIQUID-PROPELLANT ENGINE CHAMBER | 2013 |
|
RU2511785C1 |
| LIQUID-PROPELLANT ENGINE CHAMBER | 2018 |
|
RU2720596C1 |
| COOLING SYSTEM OF LIQUID-PROPELLANT ENGINE CHAMBER | 2013 |
|
RU2511942C1 |
