A gas turbine engine comprising a core gas generator engine for generating combustion gases, an additional power turbine, an additional fan section, and a booster compressor is disclosed. The power turbine includes first and second counterrotatable turbine blade rows effective for rotating first and second drive shafts, respectively. The fan section includes a first fan blade row connected to the first drive shaft and a second fan blade row connected to the second drive shaft. The booster compressor includes a first compressor blade row connected to the first drive shaft and a second compressor blade row connected to the second drive shaft.

High bypass ratio counterrotating turbofan engine

A gas turbine engine having a core gas generator engine for generating combustion gases, with an additional power turbine, an additional fan section, and a booster compressor. The power turbine includes two counter rotatable turbine blade rows which are alternately interdigitized and serve to rotate counter rotating first and second drive shafts, respectively. The fan section also includes counter rotating spaced apart fan blade sections which are respectively connected to the first and second drive shafts. A booster compressor is axially positioned between the spaced apart fan sections. The booster compressor likewise includes first and second blade rows which are counter rotating alternately interdigitized and are likewise driven by the first and second drive shafts. The engine is supported from the two frames to permit the nacelle to be non-structural. The core engine is a modular unit so that it can be separable from the counter rotating turbine, fans and booster.

High bypass ratio counterrotating gearless front fan engine

One aspect relates to a hybrid propulsive technique, comprising providing at least some first thrust associated with a flow of a working fluid through at least a portion of an at least one axial flow jet engine. The hybrid propulsive technique includes extracting energy at least partially in the form of electrical power from the working fluid, and converting at least a portion of the electrical power to torque. The hybrid propulsive technique fiuther includes rotating an at least one substantially axial-flow independently rotatable compressor rotor at least partially responsive to the converting the at least a portion of the electrical power to torque.

Hybrid propulsive engine including at least one independently rotatable compressor rotor

A turbojet having a multistage axial compressor with contrarotating blade wheels fitted on inner and outer contrarotating rotors driven in opposite directions by respective turbine wheels. Each blade wheel (105) of the outer compressor rotor is associated with a rotating shell (86, 81, 82) having relatively few thick spokes for transmitting the drive from the turbine wheel, thereby leaving the blades to transmit aerodynamically induced forces only.

Turbojet with contrarotating wheels

One aspect relates to a hybrid propulsive technique comprising providing at least some first thrust associated with a flow of a working fluid through at least a portion of an at least one axial flow jet engine. The hybrid propulsive technique comprises extracting energy from the working fluid that is at least partially converted into electrical power, and converting at least a portion of the electrical power to torque. The hybrid propulsive technique further comprises rotating an at least one independently rotatable propeller/fan of at least one rotatable propeller/fan assembly at least partially responsive to the converting the at least a portion of the electrical power to torque, wherein the rotating of the at least one independently rotatable propeller/fan of the at least one rotatable propeller/fan assembly is arranged to produce at least some second thrust.

Hybrid propulsive engine including at least one independently rotatable propeller/fan

1,233,718. Gas turbine ducted fan engines; driving compressors. SOC. NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION. Dec. 11, 1968 [Dec. 14, 1967], No.59031/68. Headings F1C, F1G and F1J. A gas turbine engine comprises an axial-flow compressor and a turbine, the compressor being divided into n co-axial units where n is two or more, each compressor unit comprising two contra-rotating rotors, and the turbine comprises (n+1) independent rotors each driving a transmission shaft, the turbine rotating in opposite directions considered from one to the next, each turbine rotor driving two rotors of two successive compressors, except for the first and last turbine rotors which each drive only one compressor rotor. In the gas turbine ducted fan engine shown in Fig. 1 the axial flow compressor assembly 7 comprises an L. P. contra-rotating compressor 11 and an H.P. contra-rotating compressor 12 and the turbine assembly 9 comprises three independent turbine rotors 13, 14, 15 each driving a shaft 26, 27, 28. The engine comprises also a ducted fan 2 upstream of the L.P. compressor. The H. P. turbine 13 is connected by shaft 26 to drive the inner rotors 22, 24 of the H.P. compressor. The L. P. turbine 15 is connected by shaft 28 to drive the outer rotor 19, 21 of the L. P. compressor, also the ducted fan 2. The I, P, turbine 14 is connected by shaft 27 and the shaft 27a which are inter-connected by spline coupling 31, to drive the inner rotor 18, 20 of the L. P. compressor also the outer rotor 23, 25 of the H, P, compressor. The bearings for the shafts are indicated diagramatically. The ducted fan engine shown in Fig. 2 again comprises three turbine stages 13, 14, 15 and two contra-rotating compressor stages 11, 12 but in this case the H. P. compressor does not comprise a rotatable outer drum or casing. The H. P. turbine 13 drives through shaft 26 an internal ring gear 58 which drives a gear 56 which in turn drives a shaft 49 carrying gears 48 which engage internal ring gears 49 carried by the compressor discs 42 which in turn carry blades 40. The L. P turbine 15 drives through shaft 28 the outer rotor 19, 21 of the L. P. compressor also the ducted fan 2. The I. P. turbine 14 drives through shaft 27 the inner rotor 18, 20 of the L. P. compressor, also through gearing 59, 57 shaft 53 and gearing 52, 47 the discs 43 and blades 41 of the I. P. compressor. In the assembly three gears 56 engage with the internal ring gear 58 each gear 56 driving a shaft 49 and gears 48; similarly three gears 57 engage the internal ring gear 59 each gear 57 driving a shaft 53 and gears 52.

Gas turbine power plants having axialflow compressors incorporating contrarotating rotors

A gas turbine unit, in particular for an aircraft turbojet engine, comprises a fan rotating coaxially in front of an axial flow compressor. The fan has an outer blading ring fixed to a rim attached to a hub of the fan through an inner blading ring, and the inner blades are pivotally attached, at the root and tip ends respectively, to the hub and to the rim about pivot axes parallel to the axis of rotation of the hub. The inner blades are all inclined in the same direction and at the same angle in relation to the hub circumference. The rim can thus expand freely under the effect of the centrifugal forces applied to it in operation by the outer blading, without local distortion and without the application of any bending stresses to the inner blades.

Jean Georges Bouiller

Papers

Gas turbine power plants having axialflow compressors incorporating contrarotating rotors

Fan for gas turbine unit