FIELD: gas-turbine engine engineering.
SUBSTANCE: flame tube comprises shell and at least one unit for supplying coolant made of openings arranged in the peripheral direction in the shell. The unit for supplying coolant is additionally provided with the grooves connected with the openings. The grooves are made in the inner side of the shell in the peripheral direction at a distance one from the other . The distance ranges from 0.5h to 3h, depth L of each groove ranges from 3h to 15h, and width S of each groove ranges from 2h to 15h, where h is the height of the groove.
EFFECT: enhanced reliability.
1 cl, 3 dwg
Title | Year | Author | Number |
---|---|---|---|
ANNULAR COMBUSTION CHAMBER OF GAS TURBINE ENGINE AND METHOD OF ITS OPERATION | 2007 |
|
RU2347144C1 |
GAS TURBINE ENGINE ANNULAR LOW-EMISSION COMBUSTION CHAMBER | 2012 |
|
RU2515909C2 |
ANNULAR COMBUSTION CHAMBER OF GAS-TURBINE ENGINE AND METHOD OF ITS OPERATION | 2007 |
|
RU2343356C1 |
ANNULAR COMBUSTION CHAMBER OF GAS-TURBINE ENGINE | 2007 |
|
RU2349840C1 |
COMBUSTION LINER OF GAS-TURBINE ENGINE | 2006 |
|
RU2343355C2 |
METHOD OF CURTAIN COOLING OF LIQUID-PROPELLANT ROCKET ENGINE CHAMBER AND DEVICE FOR REALIZATION OF THIS METHOD (VERSIONS) | 1998 |
|
RU2135809C1 |
COOLING METHOD FOR FLUE TUBE GAS-TURBINE PLANT COMBUSTION CHAMBER | 1990 |
|
RU2028550C1 |
FIRE TUBE OF INTERNAL COMBUSTION GAS-TURBINE ENGINE | 1984 |
|
SU1176678A1 |
ANNULAR COMBUSTION CHAMBER OF GAS-TURBINE ENGINE | 0 |
|
SU1719801A1 |
COOLING SYSTEM OF LIQUID-PROPELLANT ENGINE COMBUSTION CHAMBER | 2013 |
|
RU2511982C1 |
Authors
Dates
2006-10-10—Published
2005-04-05—Filed