BYPASS CHANNEL BETWEEN INNER AND OUTER LOOPS OF GAS TURBINE ENGINE (VERSIONS) ANS GAS BYPASS DEVICE COMPRISING SAID CHANNEL, GAS TURBINE AND AIRCRAFT ENGINES Russian patent published in 2010 - IPC F02K3/75 

FIELD: engines and pumps.

SUBSTANCE: gas turbine engine bypass channel arranged between inner loop forcing air to combustion chamber and outer loop comprises first section of the wall constricting bypass channel bore on the first side and located along the flow ahead of said bore, and second section of the wall constricting bypass channel bore on the second side and located opposite the first one. Channel walls of the engine blading section is arranged across bypass channel bore, in fact, on one level. Said first and second section of the wall terminate in different positions in direction of bypass channel bore length that creates irregularity of flow distribution through bypass channel bore. In compliance with one of the versions, one of said two wall sections: extends above adjacent surfaces of the structure. Note here that wall extending structure forms elongated ledge along appropriate bypass channel bore side. In compliance with one of the versions, one of said two wall sections: is buried extends relative adjacent surfaces of the structure. Note here that wall buried structure forms elongated ledge along appropriate bypass channel bore side. The other inventions of the group relate to gas bypass device, gas turbine an aircraft engines that incorporate above described bypass channel.

EFFECT: invention allows gas bleeding or injecting in gas turbine engine loops.

20 cl, 12 dwg