FIELD: gasifying cryogenic fuel in aircraft gas-turbine engines. SUBSTANCE: heat exchanger has parallel tubes connected by means of inlet and outlet collectors and arranged in shell which forms cavity with inlet and outlet for heat-transfer agent. According to invention, heat exchanger is mainly used for gasifying cryogenic fluid flowing inside tubes; tubes are located at pitch S at outer diameter of dout; tubes are mounted in groups at pitch between groups of S1 found from the following relationship 1,5≤S1/dout≤2,5 at pitch S found from relationship 1,5S/dout≥. EFFECT: enhanced efficiency; reduced external resistance; avoidance of freezing on side of heat- transfer agent. 2 cl, 3 dwg
Title | Year | Author | Number |
---|---|---|---|
GAS LIQUEFYING PROCESS | 2000 |
|
RU2204771C2 |
CRYOGENIC PUMP TEST STAND | 2000 |
|
RU2213264C2 |
TURBOPUMP SET | 1999 |
|
RU2169862C2 |
ANNULAR COMBUSTION CHAMBER | 1996 |
|
RU2161756C2 |
GAS TURBINE DRIVE OF LIQUID-PROPELLANT ROCKET ENGINE | 1999 |
|
RU2168051C2 |
BRUSH-TYPE SEALING FOR COMPRESSOR | 2000 |
|
RU2232324C2 |
TURBOPUMP SET | 1999 |
|
RU2175407C2 |
TURBOPUMP SET | 1999 |
|
RU2169293C2 |
GAS-TURBINE ENGINE FUEL-FEED CONTROL METHOD | 1997 |
|
RU2162953C2 |
METHOD OF CHECKING TURBOPUMP SET BEARING FOR WEAR | 1999 |
|
RU2175411C2 |
Authors
Dates
2001-12-27—Published
1999-11-01—Filed