Bypass gas turbine aeroengines and exhaust mixers therefor

Details Bypass gas turbine aeroengines and exhaust mixers therefor Bypass gas turbine aeroengines and exhaust mixers therefor

1984-04-09

1985-10-22

Croyle, Carlton R.

Power plants

Reaction motor

Air passage bypasses combustion chamber

60264, 181220, F02K 138, F01N 114

Patent

active

045480346

ABSTRACT:
A bypass gas turbine aeroengine has an exhaust mixer of the lobed type. The trailing edges of the confronting sides of each lobe are cut back to form notches or scallops in the sides of the lobe. To reduce aerodynamic losses and engine length and weight, the final turbine stage within the engine core is without outlet guide vanes so that the turbine exhaust gas stream issuing from the turbine has a substantial swirl component of velocity. Correction back to an axial direction of mean flow at the downstream end of the exhaust mixer nozzle is achieved by making the area of the scallop in one of the confronting sides of each lobe greater than the area of the scallop in the other side, the arrangement being such that sufficient of the turbine exhaust stream effuses from the larger scallops in directions contrary to the swirl component of velocity to produce the desired correction.

REFERENCES:
patent: 4045957 (1977-09-01), Di Sabato
patent: 4147029 (1979-04-01), Sargisson
patent: 4302934 (1981-12-01), Wynosky et al.
patent: 4401269 (1983-08-01), Eiler

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