Power plants – Combustion products used as motive fluid – Multiple fluid-operated motors
Patent
1981-01-16
1983-09-20
Casaregola, Louis J.
Power plants
Combustion products used as motive fluid
Multiple fluid-operated motors
F02C 310
Patent
active
044047940
DESCRIPTION:
BRIEF SUMMARY
BACKGROUND OF THE INVENTION
This invention relates to a compressed air turbogenerator adapted to supply for example the reaction blades of the rotary wing of a helicopter.
Nowadays, turbo-generators performing such a function have their compressors alined with and following the turbo-reactors by which they are driven.
SUMMARY OF THE INVENTION
The object of the invention is to substantially reduce the length of the turbo-reactor/turbo-compressor assembly in order to enhance the efficiency, to avoid vibrations and to facilitate the cooling of the bearings.
Consequently, according to the invention, the longitudinal axes of the turbo-reactor and of the turbo-compressor respectively are converging. Such an arrangement allows the turbo-compressor to be located under the turbo-reactor.
BRIEF DESCRIPTION OF THE DRAWINGS
Other features and advantages will result from the following description and claims.
The single FIGURE of the drawing shows in section a turbo-reactor/turbo-compressor assembly according to the invention.
DESCRIPTION OF THE PREFERRED EMBODIMENT
As shown in the FIGURE, the turbo-generator includes a turbo-reactor 1 and a turbo-compressor 2 located one above another, but with their longitudinal axes in a converging relationship.
The gas exhaust manifold 1a is provided with a rearwards extending therefrom curved manifold 1b, the rear transverse plane 1c of said curved manifold being perpendicular to the longitudinal axis of the turbo-compressor.
A cylindric sleeve 1d followed by another curved manifold 1e extends from the manifold 1a beyond said plane.
However, the curvature of said other curved manifold 1e is opposite to that of the curved manifold 1b.
A driving turbine including a crown of fixed blades 1f and a rotary wheel with driving blades 2a mounted on the shaft 3 of the compressor are located within said cylindric sleeve 1d.
The shaft 3 is rotatingly mounted through an oscillating ball bearing 4, within a tubular part as member 5 which extends from the casing 6a of the body 6 of the compressor 2.
Ball bearings 7 and 8 are inserted between said shaft and the fixed parts of the compressor.
The tubular part 5 is provided at its rear end with a spherical head 5b accomodating the ball bearing 4 and forming a ball joint with the spherical portion of the crown 1g which supports the fixed blades 1f.
In its rear part located within the curved manifold 1b, the tubular part 5 is surrounded by a coaxial sheath which delimits therewith an annular space 10.
In front of the head 5b, and accordingly close to the ball bearing 4, said space 10 is connected to a pipe 11 which supplies thereto high pressure air from the compressor of the turbo-reactor, said air thus providing for the cooling of said rear ball bearing.
In order to compensate for the effects of the expansion, the body 6 is supported by the turbo-reactor through a hinged rod or member 12.
The blade wheel is keyed at the end of the shaft 3 and rotates in the compression chamber and provides for suction of air through the central aperture 6b.
The air is further discharged by the blade wheel through the lateral apertures 6c connected to the distribution chamber 13 which is directly connected to the rotor of the rotary wing through the supply duct 14.
In contrast with the conventional helical chambers, the distribution chamber of the arrangement according to the invention has a constant radial cross section so as to avoid the turbulences of the air which is discharged therefrom at a pressure of about 3 bars.
The invention is applicable more particularly for supplying the reaction blades of the rotary wing of a helicopter and in any case where a high pressure flow is desired.
In fact, one can observe that owing to the derivation of high pressure air (for example at 5 kg/cm2) from the compressor of the turbo-reactor 1 and to the supplying thereof into the annular space 10 through the pipe 11, the pressure of said air when it reaches the chamber 13, is added to the pressure of the turbo-compressor (for example 3 kg/cm2).
1. A compressed air turbo
REFERENCES:
patent: 2150670 (1939-03-01), Bentley
patent: 2333053 (1943-10-01), Stroehlen
patent: 2744722 (1956-05-01), Orr
patent: 4193262 (1980-03-01), Snell
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