Gas turbine jet propulsion engine

Claim 2

A by-pass gas turbine jet propulsion engine comprising in flow series independently rotatable low and high pressure axial flow compressors, combustion equipment, independently rotatable high and low pressure turbines drivingly connected to the high and low pressure compressors respectively, an exhaust duct, a by-pass duct which is arranged to receive at its upstream end a proportion of the air compressed by the low pressure compressor, a mixing device providing a large area of communication between the downstream end of said by-pass duct and said exhaust duct, reheat combustion equipment disposed in said exhaust duct downstream of said mixing device, the low pressure turbine having at least one stage of variable nozzle guide vanes and the exhaust duct having an outlet nozzle of variable effective area, said low pressure compressor and said low pressure turbine having their rotational speed controlled by controlling said nozzle guide vanes and said outlet nozzle, said low pressure compressor having an outlet end which has an annulus area which is larger than conventional for efficient operation of said low pressure compressor at the higher rotational speed end of its useful speed range, the annulus area of said low pressure compressor decreasing toward the high pressure end of the compressor to an extent such that the compressor has substantially uniform flow velocity from its inlet to its outlet end at approximately the center of its useful speed range, and said low pressure compressor having a plurality of stages, at least the stage nearest the high pressure compressor being provided with a stage of variable incidence stator blading whereby the low pressure compressor is adapted to pass a relatively high mass flow at lower rotational speeds of its useful speed range, the effective by-pass ratio of the engine being controlled by controlling the rotational speed of the low pressure compressor and turbine and effective area of the outlet nozzle.

Claim 3

An engine as claimed in claim 1 in which a row of nozzle guide vanes is mounted upstream of the low pressure turbine, at least part of each nozzle guide vane being movable to vary the effective area of the low pressure turbine nozzle and thereby, in conjunction with the variable outlet nozzle, control the low pressure turbine speed.

Claim 4

An engine as claimed in claim 2 in which the low pressure turbine nozzle guide vanes have fixed upstream portions and hinged trailing edge portions whereby, in addition to varying the effective turbine nozzle area, movement of the trailing edge portions varies the effective angle of incidence of the gases entering the low pressure turbine.

Claim 5

An engine as claimed in claim 1 in which an intermediate pressure axial flow compressor is disposed upstream of the high pressure compressor and downstream of the entry to the by-pass duct, said intermediate pressure compressor being driven by an independently rotatable intermediate pressure turbine disposed between the low and high pressure turbines.

Claim 6

An engine according to claim 4 in which the low, intermediate and high pressure turbines are drivingly connected to the respective low, intermediate and high pressure compressors by respective coaxially arranged shafts, the outermost shaft being connected to the high pressure turbine and the innermost shaft to the low pressure turbine.

Claim 7

An engine as claimed in claim 4 in which the intermediate and low pressure compressors in operation of the engine run at substantially constant corrected rotational speed.

Claim 8

An engine as claimed in claim 1 in which a row of inlet nozzle guide vanes for the high pressure turbine is mounted within the combustion equipment, the said guide vanes having hollow interiors and apertures in their walls through which dilution air is introduced into the hot combustion gases.

Claim 9

In a by-pass gas turbine jet propulsion engine of the type including in flow series independently rotatable low and high pressure axial flow compressors, combustion equipment, independently rotatable high and low pressure turbines drivingly connected to the high and low pressure compressors respectively, an exhaust duct, and a by-pass duct which is arranged to receive at its upstream end a portion of the air compressed by the low pressure compressor the improvement comprising: a mixing device which provides a large area of communication between the downstream end of said by-pass duct and said exhaust duct; reheat combustion equipment disposed in said exhaust duct downstream of said mixing device; and means for controlling the effective ratio of the amount of air passing through said by-pass duct to the amount of air passing to said combustion equipment so as to produce efficient operation at cruise speed as well as high thrust when needed, said means comprising (a) at least one stage of variable nozzle guide vanes in said low pressure turbine and means for adjusting said variable nozzle guide vanes, (b) said low pressure compressor having an outlet end which has an annulus area which is larger than conventional for efficient operation of said low pressure compressor at the higher rotational speed end of its useful speed range, the annulus area of said low pressure compressor decreasing toward the high pressure end of the compressor to an extent such that the compressor has substantially uniform flow velocity from its inlet to its outlet end at approximately the center of its useful speed range, said low pressure compressor having a plurality of stages, at least the stage nearest said high pressure compressor having a stage of variable incidence stator blading whereby said low pressure compressor is adapted to pass a relatively high mass flow of air at lower rotational speeds of its useful speed range, and means for adjusting said variable incidence stator blading, and (c) an exhaust nozzle of variable effective area receiving mixed by-pass air and combustion products from said exhaust duct and means for varying said effective area, whereby cruising of the aircraft in which the engine is mounted at supersonic and subsonic speeds is effected efficiently by operating said low pressure compressor at relatively low speed so as to produce a high by-pass ratio, and whereby high thrust is effected by operating said low pressure compressor at relatively high speed so as to produce a low by-pass ratio.

Claim 10

In a by-pass gas turbine jet propulsion engine of the type including in flow series independently rotatable low and high pressure axial flow compressors, combustion equipment, independently rotatable high and low pressure turbines drivingly connected to the high and low pressure compressors respectively, an exhaust duct, and a by-pass duct which is arranged to receive at its upstream end a portion of the air compressed by the low pressure compressor the improvement comprising: a mixing device which provides a large area of communication between the downstream end of said by-pass duct and said exhaust duct; reheat combustion equipment disposed in said exhaust duct downstream of said mixing device; and means for controlling the effective ratio of the amount of air passing through said by-pass duct to the amount of air passing to said combustion equipment so as to produce efficient operation at cruise speed as well as high thrust when needed, said means comprising (a) at least one stage of variable nozzle guide vanes in said low pressure turbine and means for adjusting said variable nozzle guide vanes, (b) said low pressure compressor having an outlet end which has an annulus area which is larger than conventional for efficient operation of said low pressure compressor at the higher rotational speed end of its useful speed range, the annulus area of said low pressure compressor decreasing toward the high pressure end of the compressor to an extent such that the compressor has substantially uniform flow velocity from its inlet to its outlet end at approximately the center of its useful speed range, said low pressure compressor having a plurality of stages, at least the stage nearest said high pressure compressor having a stage of variable incidence stator blading whereby said low pressure compressor is adapted to pass a relatively high mass flow of air at lower rotational speeds of its useful speed range, and means for adjusting said variable incidence stator blading, and (c) an exhaust nozzle of variable effective area receiving mixed by-pass air and combustion products from said exhaust duct and means for varying said effective area, whereby cruising of the aircraft in which the engine is mounted at supersonic and subsonic speeds is effected efficiently by operating said low pressure compressor at relatively low speed so as to produce a high by-pass ratio, and whereby high thrust is effected by operating said low pressure compressor at relatively high speed so as to produce a low by-pass ratio.