US2350839A

US2350839A - Machine for compressing gases by centrifugal effect

Info

Publication number: US2350839A
Application number: US382283A
Authority: US
Inventors: Szydlowski Josef
Original assignee: Individual
Current assignee: Individual
Priority date: 1940-04-08
Filing date: 1941-03-08
Publication date: 1944-06-06
Anticipated expiration: 1961-06-06

Description

J. SZYDLOWSKI June 6, 1944.

MACHINE FOR COMPRESSING GASES BY CENTRIFUGAL EFFECT Filed March 8, 1941 .Fi6.1. fie-.2.v

INVENTOR: JOSEF SZYDLOWSKI BY ,oii g ATTORNEKS Poiented June e, 1944 MACHINE roa comrnass mc cnsrnmocsr. nrrnc Gases, a! 'r Josef Sndlowski, Saint re de 3mm, 1mm: vested in the Alien Property Custodian Application 4 Claims.

The present invention concerns machines for compressing gases by centrifugal effect, such as turbo-compressors and in particular the turbocompressors utilised for supercharging the internal combustion engines on board'aircraft.

Machines of this kind impart to the gas sucked in, a vis viva which is converted into static energy or pressure at the outlet.

It has been attempted, in all the applications of these machines, to obtain ,a high compression ratio, for a minimum bulk and weight, with an output as high as possible.

The invention satisfies these conditions by including upon one and the same rotor in a single machine with concentric rings of blades having diameters increase fromthe inlet port to the outlet port, and between which rings are arranged rings of adjustable blades.

The accompanying drawing illustrates by way of example only, some forms of apparatus embodying the salient features of my invention.

Fig. 1 of .the accompanying drawing is 8. diagram of a known type of machine shown in axial half-section.

Fig. 2 is an axial half section of a machine made according to this invention.

. Fig. 2a is a partial end view showing certain ring detail.

Fig. 3 is another partial end view showing blade arrangement.

Figs. 4, 5 and 6 are views similar in character to Fig. 2, showing modifications.

Fig. 7 is an enlarged vertical section on the line 1-1 of Fig. 2a, showing the details'of the ccntgol means for one of the racks of Figs. 2 and a.

In the embodiment illustrated in Fig. 4, the

gas, for instance sin-sucked in through an inlet orifice 0 is drawn along in a rapid rotary movement by the blades of a rotor R. and ejected at high speed into a manifold V or recovery volute March 8, 1941, Serial No. 382,288

France April 8, 1940 working one after the othenc'lhat of the second which are arranged fixed rings of blades which are simply guiding blades. when a compressor of high compression ratio thus devised is coupled to the engine of an aircraft, serious inconveniences generally result therefrom. The delivery pressure of the compressor from the groundup to the altitude at which the. engine must have its optimum power, is limited by the detonation of the engine. .As the engine rotates at'constant speed, it results therefrom that the pressure of the compressor is too high from the ground up to the altitude'in question. It is then necessary, either to eliminate a portion of the pressure by means of valves, which corresponds to a costly destruction of the energy suppliedby the engine, or to provide complicated and heavy change speed mechanisms, in order to cause the working speed of the compressor to vary according to the altitude, whereas the working speed of the engine remains constant.

The applicant has already disclosed in his United States Patent No. 3.210.155 a solution for chamber. Between the rotor and volute chamber of manifold V, is interposed a suitable fixed blade D or diifuser, the function of which is to increase the output of the conversion of the vis vivaof the air into static pressure.

: The compression ratio between the inlet and the outlet increases with the angular speed of the rotor, This speed has for upper limit, the value which corresponds to a linear speed of the air at the end of the bladeredual to the'local speed of sound. Beyond this speed, the output' of i the machine rapidly lowers.

For avoiding this obstacle, it has been proposed to couple in several stages, with several machines remedying this inconvenience. This solution consists in providing, before the admission of air into the rotor, settable shutters as-shown' at E .in Fig. 4 of the drawing annexed to the present application. The air passes through said shutters towards the centre of the machine. In pro- 7 portion as the shutters are inclined, the speed of rotation they impart to the air increases in proportion as said air approaches the centre of the machine. This increase is limited by the speed, of sound which constitutes an upper limit. Said considerable reduclimit is rapidly reached and a tion in the output results therefrom.

The present invention allows of obtaining a high compression ratio and is adaptable to the most varied conditions or flight without giving rise to the above mentioned inconveniences.

Amachine improved according to theinven- .tion causes the air to be subjected to an evolutioncomparable to that to which it is subjected in. known compressors having several stages.

' shock to. the inlet of the set of, blades A to that produced by the ring V The air delivered by the first-rotating ring, approaches the intermediate fixed blades which slow it down, the effect of which is to increase its static pressure.

' The admission of the air into the second ring of rotating blades takes place at this static pressure and the kinetic energy imparted to the mass or air in said second rotating ring is again con! verted into pressure in the following flxed ring. The pressure thus increases from one to the otheras" in known multi-stage machines.

The rotor of the machine as shown in Fig. 2 comprises three rings or concentric sets of blades the outlet oi! the set of blades A a is the angle corresponding to the air streams after they have been deviated by the fixed set of blades V It willimmediately be seen that if a is smaller than a ,'the movement of 'the air is slowed down and a part of its kinetic energy is converted, by the set of blades V into potential energy. on

the other hand, it will be seen that the set of blades of the stage immediately following A, is fedwith a lower circumferential speed (pro'portional, for an equal output, to tangent a). The application of the theorem of the impulse moments then showsthat the increaseof pressure produced by the set of blades A is so much the greater as is smaller. The conclusion is the reverse if a is greater than a.

If theblades of the nxed rings V and V are pivotally mounted on suitable spindles-by setting them accordingly, the rotating set of blades immediately following them can be charged or discharged at will.

when the invention is applied to the supercharging of an aeroplane engine, from the ground up to the so-called balance altitude, this circumstance is particularly advantageous. The.

Two rings of blades V and V are assasso can be done away with and the intermediate blades V between both stages need only be maintained as regulating system. In this case the helical wheels E are preceded only by an axial or radial axial channel provided or not with a flxed guiding set of blades.

The control of the orientation or setting of the 7 blades such as V V can be obtained by any suitablerneans superfluous to illustrate in the various embodiments.

The admission of air can also be eifected through a volute.chamber E, opening into an axial or radial channel (Fig. 5). The inlet shutters E are done away with and the angle of incidence of the first helical or inclined blade wheel E is constant. Its value results from the suitable adaptation of the main section of the volute chamber to that of the channel. This method of construction is more particularly suit ed to radial type engines.

A single-stage and simply radial compressor can also be devised (Fig. 6) obtained by doing away with all the driving members preceding the fixed intermediate sets of blades V except the blades A. The admission of air takes place, in this case through the axial channeloccupied by the helical or inclined blade wheels E in the preceding examples. This channel can open directly tothe free air or be connected to an inlet voiute chamber or to a radial channel.

Fig. 2a is a partial end view corresponding. to Fig. 2 and shows two toothed rings I and 2 which can rotate on bearings of the casing of the compressor and mesh with pinions 4 respectively fast on each of the blades of the rings V and V The toothed rings or racks i and 2 are controlled by

levers

5 and 8 pivoted at I and I, respectively. and acting by their fork-shaped'end on a flnger 9 of each ring. Both levers can be controlled separately or in combination by a link-work II which is manually or automatically acted upon from a pressure-gauge, for instance.

required compression ratio is in fact very vari- 1 able according to the altitude at which the aero;

justed in such a manner that they slow down the air or accelerate it. The following set of blades (A or A might then be discharged, even until the apparatus operates as a'turbine.

The torque received from the engine will thus be reduced to the strict minimum necessary for .upplying the engine atits nominal pressure. This reduction of the torque is so much the more substantial as the aeroplane flies at a lower altitude.

plane is flying. The blades V and V' can be ad-- By limiting the number of stages to two, I

compressor of the present invention has a diametral cumbersomenes's equal or scarcely greater than a single-stage compressor of the same care gory. The longitudinal cumbersomeness I the same as that of a slngle-stage'machine.

The adjustment by means of the Fig. 7 shows on an enlarged scale, as already indicated, the detail of the control of a ring i or 2 o! the other views, such as Figs. 2 and 2a, for example.

what I claim as my invention and desire to.

secure by Letters Patent is:

1. In a centrifugal turbo-compressor, a casing having an inlet port and an outlet port for the fluid, and a plurality of radially spaced concentric sets of guide blades having substantial axial and radial extent, a rotor mounted in said casing concentric with said sets of guide blades, and having a plurality of radially spaced sets of impeller blades interposed between said radially spaced sets of guide blades, each of said guide blades being adjustable about an axis parallel to the rotor axis.

2. In a centrifugal turbo-compressor, a casing having an inlet port and an outlet port for the fluid, and a plurality oi radially spaced concentric sets of guide blades having substantial axial and radial extent, arotor mounted in said casing concentric with said sets of guideblades, and having a plurality of radially spaced sets of impeller blades interposed between said radially spaced sets of guide blades, each of said guide blades being adjustable about an axis parallel to the rotor axis, and means for adjusting said guide blades. I a

3. In a centrifugal turbo-compressor, a casing having ,an inlet port and an outlet port for the fluid, a plurality of settable guiding shutters adn 7 Jacent' the inlet port, a plurality of fls'ed diflusing blades adjacent the outlet port, and a plurali of radially spaced concentric sets 0! guide blades having substantial axial and radial extent. between said shutters and said diilusing blades, a rotor mounted in said casing concentric with said sets of guide blades and having a plurality of axially spaced sets of radial blades having axial action upon the fluid, anda plurality of radially spaced sets of impeller blades interposed l0 spect to the rotor axis to cause axial flow oi the between said radially spaced sets 0! guide blades,

each of said guide blades belnsadiustablc about i an axis parallel to the rotor axis.

4. In a centrifugal turbo-compressor, a casing having an inlet port and'an outlet port iorthe fluid, a guiding volute chamber at said inlet port is a'asaaso I I 3 for impartin: to the iluid a rotation component. a plurality of radially spaced concentric sets of suide blades havin: substantial axial and radial extent, adiustably mounted in said casing, aplus .rality of .diflusing blades fl'xed in said casing ad- Jaoent the outlet port, a rotor mounted in said,

N casing concentric with said sets of guide blades, a plurality of axially spaced sets of radially proiecting. blades on said rotor and inclined with reiiuid, and 'a plurality oi radially spaced sets of impeller blades on said rotor-interposed between said radially spaced sets oi guide blades to cause centrifugal now of the fluid.

' JOBEF BZYDLQWSKI.