US2509555A - Compressor turbine - Google Patents

Description

May 30, 1950 YQUHQUSE 2,509,555

COMPRESSOR TURBINE Filed Dec. 4, 1946 3 Sheets-Sheet 1 I HQ:

INVENTOR. JOSEPH YummusE Y ATTORNEY 3 Sheets-Sheet 2 J. YOUHOUSE COMPRESSOR TURBINE May 30,

Fil ed Dec. 4, 194a May 30, 1950 .1. YOUHOUSE COMPRESSOR TURBINE 3 Sheets-Sheet 3 Filed Dec. 4, 1946 km Pm INVENTOR. JusBPH YZnmnusE AT TORNEY Patented May 30, 1950 s 'PATE NT, orr ca oomra'sssoa 'rmumm Joseph Youhoule, l'alrileld, Conn. Application nmaw 4, 1m, Serial No. nasal "Claims. (on. re-41) This invention relates to new and useful improvements in power plants utilizing explosive ins] and has particular relation to a compressor turbine.

An object or the invention is to provide a compressor turbine providing-tor a relatively high compression ratio in a single stage.

Another object is to provide a compressor tunbine wherein the fuel is compressed by centrifugal action and by a. further positive action prior to and at the time oi ignition.

Another object is to provide a compressor turtime so constructed as to provide for centrifugal and positive displacement compression of the i gases obtained inone stage by therelative movement of two rotating elements. 7

An additional object is to provide a compressor turbine including centrifugal impellers for movement of the explosive gases to compression and bring chambers.

Another object is to provide a turbine eompressor having the attribute of high thermal emciency because of the immediate impincins of the combustion pressures on the turbine blades without excessive thermal and frictional losses.

Yet another object is to provide a compressor turbine which will 0 because the combustion gases act on the turbine blades during somewhat less than one-half of the rotatinaarc.

Yet another object is to provide a compressor turbine including a pair of rotating elements locked together by continually meshing star and internal users and wherein the othercomponents while in extremely slightly spaced relation are stationary casing perate at a safe temperature I not in mechanical contact whereby there is no mechanical wear and the unit is tree or lubricating problems and is inherently quiet and has a low service requirement. c

Other objects and advantages of the'invention will become apparent from a consideration or the following detailed description taken in connection with the accompanying drawings wherein a satisfactory embodiment of the invention is shown. However, it is to be understood that the invention is not limited to the details disclosed but includes all such variations and modifications aetallwlthin the spirit of the invention andthe scope of the appended claims.

In the drawings: 5 r

Fig. l is a side elevatlonal view looking at the exhaust side of an engine constructed in accordance with the invention;

Fig. 2 is an edge elevatlonal view of the engine;

2 Fig. 3 is a central vertical sectional view through the engine;

llig. 4 is a view looking the compression chamber element or the engine;

Fig. 5 is a somewhat similar view looking at the outer side of what may be termed the piston elemental the engine;

Fla". 6 is a detail elevational view showing a portion or the element of Fig. 5 but looking from the opposite side thereof;

Fig. 'l is a developed view taken as along the line l-'l orFig. 8; p i

Fig. 8 is an enlarged detail sectional view takon as along the line 8--t of Fig. 4;

Fig. 9 is a detailed view in elevation show-ins the manner or mounting turbine blades on a ring or carrier; and

Fig. loisan elevatioual view suggesting a manner of forming the turbine blades.

Referring in detail to the drawings, my improved engine is shown as including an outer generally designated in and comprising a substantially circular mid section l l, aclosure and bearing section side of the. section ll, as at l3, and a. closure and bearing section l4 bolted to the other side of the mid section. as at l5. section may have less or a base it secured thereto or integral therewith and adapted to be bolted or otherwise fastened to any suitable support not shown). The closure and bearing member it may conveniently include an exhaust manilold ll to which an exhaust pipe is is shown secured as by bolts 59. On their outer surfaces; the housing or casing parts II and it are shown as provided with heat dissipating vanes so.

into an open. side of or cylinder carryinl Within the casing or housing described there 7 3i and 22 are secured to shafts 23 and ll, re

ntthrough a sleeve 2 secured to the cover member -j pectively.

' Shaft 21 is secured in element 2! and in; 26 provided a hub portion 25 01' the passes outwardly through a bearin the cover member I! and then I and an outer bearing means 28 located in a cylindrical hub With particular attention to Fig. 3, it will be noted that the shaft 23 is located at an uncle to the horizontal and this is the permanent posil2 bolted to one- At its lower side the mid qulpped with turbine blades and fully appear. Elements dike housing 2! I! .as by bolts 3|. I

tion of the shaft. Moreover, the'element 2| is located normal to the axis of the shaft 23 whereby said element is at a slight angle to the vertical.

On the inner end of the hub 26 is a star gear 3|, the purpose of which willbe set forth. Ex

tending radially from said hub are a series of vanes or impellers 32 relieved at their inner ends to clear the. gear 3|. hub, a wall 33 is located over the outer edges of the vanes or impellers 32 and as shown is formed integral with them. This wall is in the nature of an annulus and at its inner periphery is turned outwardly as at 34 leaving a space 35 between the hub and the wall for the entrance of a combustible mixture admitted to the casing It as through an intake port 39 provided in the hub-like portion of the cover l2.

At the outer ends of or beyond the vanes 32, the wall 33 is carried inwardly at a number of spaced points providing an annular series of pistons 31 extending from the inner side of the element 2|,

towardthe outer edge of such element. The pistons 31 have their adjacent ends in slightly spaced relation, the space between such ends being indicated at 33 and being in the nature of pockets or recesses. As herein shown, the pisdevice and effecting economy in the use of material. As best shown in Fig. 5, the vanes or impellers 32 are slightly offset from direct radial lines with respect to the hub 23. This is to provide for relative movement of such vanes or impellers at the sides oi. vanes or impellers of the element 22 as will later fully appear. I

The element 22 includes a hub portion 39 rigid with the inner end of the shaft 24 and such shaft extends outwardly through a bearing 49 located within a central portion of the cover member l4 and then through a sleeve 4| and a bearing 42 located within a tubular housing 43 extending centrally and horizontally outwardly from the cover member I4 and secured thereto as by bolts or the like 44. It is noted that the shaft 24 is arranged horizontally and that the element 22 is normal to the shaft or vertical. Thus, the shaft 23 and its element 2| are arranged in a slightly oilset or angular relationship to the shaft 24 and its element 22.

In addition to its hub-like portion 39, the element 22 includes a radially extending web-like portion 45 shown as concavo-convex in transverse section (see Fig. 3) and on its outer peripheral edge provided with a wall-like flange 46. On its forward side or on its side toward the element 2 I, the web-like portion 45 of element 22 is provided with a series of vanes or impeller blades 41 including extensions or extension-like portions 48 carried beyond the wall 46.

These extensions 48, together with the wall portion 46 and an inwardly directed annular flange 49 carried by the casing section II and the portion of said casing section immediately forward oi said flange 49, define a series of cylinders or pockets 60 each of a size slightly greater than the size of one of the pistons 31. It will be understood that as the flange 49 and, in fact, the entire casing section I I is stationary, that portion of the flange forming the outer portion of the rear wall of any particular cylinder 50 and that portion of the outer annular wall of section II forming the outer limit of any particular cylinder is constantly changing when the engine is in operation as at such time the elements 2| and 22 are rotating with their shafts 23 and 24.

In spaced relation to the v A series of bolts 3| serve to secure three rings 52, I3 and 34 in. a semi-nesting relation and to,

the wall or flange 43. Of these rings, the rings acting on the blades 56 and 66. As these latter blades are driven by said products of combustion, the element 22 carrying such blades as well as the element 2| is rotated.

The impeller blades or vanes 41 of the element 22 extend radially with respect to the hub-like "tons are hollow thus reducing the weight of the portion 39 and laterally with respect to the weblike portion 43 of said element, and in the assembly, the relationshipoi' these blades orvanes to the blades or vanes 32 of element 2| is a side- 'by-side relation, although a close side-by-side renation. This is made apparent froma comparison of Figs. 5, 6 and '1 as it is noted that the extensions 43 of. the blades 41 are at certain times received in the recesses 33 between the pistons 31. Such recesses are offset but slightly laterally of the blades or vanes 32 and, in fact, one edge of each recess may be substantially flush with one side or edge of a vane.

In the forward side of its hub portion 39, the element 22 is slightly recessed, as at 69. and against the outer annular wall of said recess, an internal ring gear 69 is flxed. This ring gear is of asize and construction to mesh with the star gear 3| carried on the hub portion of the element 2|. Due to this meshing oi the gears and to the relationship of the vanes or blades 32 with the vanes or blades 41, the elements 2| and 22 rein the neighborhood of .010 inch and this is therelationship preferably existing between the pistons 31 and thewalls of the cylinders or recesses 69.

As shown in the drawings, the firin position for each cylinder 50 and each piston 31 is at the bottom of the engine. At the flring position, a recess 6| is provided in the flange 49 forming a slight enlargement of a cylinder at this point and communicating with said recess is an ignition device as the spark plug generally designated 32. As here shown, the elements 2| and 22 are designed to rotate in the direction indicated by the arrow 63, in Fig. 4, and immediately beyond the .firing chamber, the Wall or flange 49 is provided with a series of ports 64 preferably arranged at an angle as shown in Fig. 7 and communicating the cylinders 59, which at any given time are over said ports, with the turbine blades.

The hot expanding products of combustion passing through said ports from-the cylinders impinge upon the turbine blades to drive the same forwardly togetherwith the entire element 22 and then impinging upon the stationary blades 61' are ll reversed and then impinge upon th blades 63 to v assist in the forward driving of the element 22. Thereaftenas here shown, such gases are exhausted into the manifold I1 and thence through the exhaust pipe it. However, it will be understood that additional sets of turbine rings and blades may be incorporated in the engine if that is desired. r

Owing to the angular relationship of the shafts 23 and and of the elements 2| and 22, it will be a preciated that in the course of rotation any given piston will be entirely out of its cylinder when said piston and its cylinder are at the top or upper side of the engine. As the elements rotate together and said piston and cylinder move downwardl along the right side of the engine, as viewed in Fig. 4, the piston. by a constant movement, enters its cylinder until when said piston and cylinder reach the bottom or lower side of the engine, at the firing chamber, the piston has entered the cylinder to the maximum depth provided for or to a point very close to the maximum depth provided for. Then, as rotation continues and that piston and cylinder move upwardly along the left hand side of the engine, as viewed in Fig. 4, the piston gradually shifts out of the cylinder until the point of maximum separation is reached at or about the top or upper side of the engine.

With the foregoing in mind, the operation of the engine is readily understood. For example, the proper fuel is fed in through the port 36 and due to the rotation of the elements 2| and 22 there is a centrifugal action tending to throw the fuel toward the outer periphery of the engine. This tendency is assisted by the vanes or impeller blades 32 and 41 with the result that there is a slight compression of the fuel toward the outer periphery of the engine and a slight compression of the fuel in any given cylinder atthe point of maximum withdrawal of the piston from the cylinder. This insures a full charge to each cylinder. In fact, it is when a piston and cylinder are re- From the above it is thought that it will be clear that a high compression ratio will be obtained with the present engine and that there is a certain compression of the fuel charge due to centrifugal action or the rotating parts and a further compression as the pistons enter their cylinders. The centrifugal compression, as well cylinders. Owing to the angular relationship of lated, as are those at the upper side of Fig. 3,

that the greater part of the charge enters the cylinder.

As the rotation progresses and th piston progressively enters a cylinder, the charge therein is progressively compressed until the point of maximum compression is reached at the firing station, or at the spark plug 62. There, the explosion having taken place, the piston is not blown out of a cylinder but can only recede therefrom during the course of the upward movement of the piston and cylinder over approximately one-half of the path of circular travel of these parts. .It is during this time that the hot expandlng gases from the cylinder, moving outwardly through the ports 84, engage the various sets of vanes and operating on the vanes and 56, impart rotative movement to such vanes and thus to the element 22.

As the element 2! is geared to the element 22 through the gears II and BI and through the overlapping relationship of the vanes or blades 32 and H, it will be apparent that the rotatable movement of the element 22 results in the identical movement of the element 2|. Owing to the high speed at which the engine rotates, the slight clearance provided between any piston and the walls of its cylinder while admitting of the loss of some fuel during the compression, does not admit of the loss of a material portion of the charge. This is due to the slight clearance provided in combination with the rapidity of motion of the rotating the element, the movement of the pistons into and out of the cylinders is obtained without the use of any actual mechanism. Because of the immediate impinging of the combustion pressures on the turbine blades, the engine has a high thermal efficiency and owing to the employment of the numerous radiating vanes and to the fact that the combustion gases act on the blades for somewhat less than one-half of the rotating arc, excessive temperatures in the parts is avoided.

As the two rotating elements 2| and 22 are locked together by the continuously meshing gears and the various portions of said elements always have a slight clearance. and are thus without mechanical contact, it will be clear that there is no reason for wear and that there are no lubricating problems in connection with the present unit which therefore has a low service requirement and is inherently quiet.

While the ignition device 62 is shown as located at the bottom or lower side of the engine,

it will be understood that the invention is not limited to this arrangement. Device or spark plug 62 will, in any construction, be located at a point of high compression and this will depend on the relation of element 2| to element 22.

For example, should the shaft 23 be arranged to incline instead of at a decline, the spark plug would be located toward the top or upper side of the engine. If the shaft is directed to one side or the otherof the vertical rather than the horizontal, the inlet and firing stations will be at one side or, the other of the vertical rather than the horizontal center.

In fact, the piston construction or piston carrying element 2| might be arranged in a definite plane, as a definite vertical plane, and the cylinder construction or element 22 may be: arranged slightly off the vertical. This would be the reverse of what is shown and described but the action or operation would be about the same. Preferably, any particular piston and its cylinder are beyond the end of the row of ports Bl prior to separation of such piston and cylinder for the admission of a new fuel charge.

1 rings.

Figs. 9 and 10 suggest a manner in which the various -turbine blades may be made and mounted on the various rings at little initial expense, as without the use of patterns and the like. The method consists in or comprises the extruding orotherwise forming of a strip or continuous length of stock of any desired size and of the proper transverse contour, as shown at 65 in Fig. 10. t

Then this stock is cut, as at 66, into suitable lengths 61. Each such length will comprise one turbine blade. Then these lengths or blades are welded or otherwise rigidly secured to one of the For example, in Fig. 9, the blades 56 are shown as welded at 68 to the ring 54. This same method or forming a length of stock of the proper transverse contour, cutting the stock into blade lengths, and then weldingthe blade lengths in proper order to a, ring or other body is followed in connection with the blades of the rings 53 and 52, as well as the ring 54.

Having thus set forth the nature of my invention, what I claim is:

1. In a compressor turbine, a stationary casing, a pair of shafts rotatably mounted in said casing, a pair of rotatable elements in said casing and mounted on the respective shafts, means whereby said elements rotate together as a unit, pistons carried by one of said elements, cylinders formed by the other of said elements, turbine blades carried by one of said elements, a firing station, said piston carrying element and its shaft mounted at an angle to the cylinder carrying element and its shaft whereby during a. portion of each revolution of the elements as they approach said firing station said pistons are moved into the cylinders and during the remaining portion of each such revolution as the elements are carried beyond the firing station said pistons are moved out of the cylinders, and means for delivering the ignited expanding fuel charge from the cylinders to said turbine blades.

2. In a compressor turbine, a stationary casing, a pair of shafts rotatably mounted in said casing, a pair of rotatable elements in said casing and mounted on the respective shafts, means whereby said elements rotate together as a. unit, pistons carried by one of said elements, cylinders formed by the other of said elements, turbine blades carried by one of said elements, a firing station, one of said elements and its shaft mounted at an angle to the other element and its shaft whereby during a portion of each revolution of the elements as they approach said firing station the pistons and cylinders are progressively telescoped and during the remaining portion of each such revolution as the elements are carried beyond said firing station the pistons and cylinders are progressively separated, and means for delivering the ignited expanding fuel charges from the cylinders to said turbine blades.

5. In a compressor turbine, a casing. a pair of rotary elements in said casing, cylinder construotions at a side of one of said elements to ward its outer peripheral edge, pistons at a side of the other element toward its outer peripheral edge, means whereby said elements rotate together, means whereby as said elements rotate they are moved bodily relatively and the pistons and cylinder constructions are progressively telescoped for a portion of a revolution and are progressively separated for the remaining portion of the revolution, turbine blades fixed to one of said elements, a fixed firing station, an ignition means at said station for igniting the fuel in the cylinders as they reach the station, and

means for impressing the expanding ignited 3. In a compressor turbine, an outer stationary casing having an outer wall portion and a central hub portion, said casing having an inlet through said hub portion for a fuel comprising a compressible explosive mixture, means within said casing and rotatable on an axis substantially concentric with said hub portion and by centrifugal action moving toward the outer portion of said casing and compressing such an explosive mixture fed through said inlet, means for thereafter further compressing the mixture by a mechanical action, a rotatable element carrying turbine blades, means for igniting the fuel following compression by said mechanical action, and means for impressing the ignited charge on said turbine blades to impart rotation to said element.

4. In a compressor turbine, a casing, a pair of rotary elements in said casing, cylinder constructions at a side of one of said elements toward its outer peripheral edge, pistons at a side of the other element toward its outer peripheral edge, means whereby said elements rotate together, and means whereby as said elements rotate they are moved bodily relatively and the pistons and cylinder constructions are progressively telescoped for a portion of a revolution and are progressively separated for the remaining portion of the revolution.

charge on said turbine blades to impart rotation to said elements.

6. In a compressor turbine, a casing, a pair of rotary elements in said casing, one of said elements having cylinder constructions at its outer peripheral edge, pistom at the outer peripheral edge of the other element, means whereby said elements rotate together, means for feeding fuel into said casing, means rotatable with said elements for impelling said fuel in a circular path within said casing as said elements are rotated whereby as said elements rotate said fuel is by centrifugal action compressed at the outer peripheries of the elements, turbine blades fixed to, one of said elements, means whereby as said elements rotate said piston and cylinder constructions are progressively telescoped for a portion of a revolution to further compress fuel in said cylinder constructions, a firing station adjacent the point of maximum telescoping of said pistons and cylinder constructions, ports beyond said firing station for delivering the ignited expanding fuel charges from the cylinders to said turbine blades for impingement of the expending products of combustion thereon to rotate the blades and elements, and said means for causing progressive telescoping of the pistons and cylinder constructions as they approach said firing station operative to progressively separate the pistons and cylinder constructions as they recede from said station.

7. In a compressor turbine, a casing, a pair of rotary elements in said casing, one of said elements having cylinder constructions at its outer peripheral edge, pistons at the outer peripheral edge of the other element, means whereby said elements rotate together, means for feeding fuel into said casing, means rotatable with said elements for impelling said fuel in a circular path within said casing as said elements are rotated whereby as said elements rotate said fuel is by centrifugal action compressed at the outer peripheries of the elements, turbine blades fixed to one of said elements, means whereby as said elements rotate said piston and cylinder constructions are progressively telescoped for a portion of a revolution to further compress fuel in said cylinder constructions, a firing station adjacent the point of maximum telescoping of said pistons and cylinder constructions, ports beyond said firing station for delivering the ignited expanding fuel charge from the cylinders to said turbine blades for impingement of the expanding products of combustion thereon to rotate the blades and elements, said means for causing progressive telescoping of the pistons and cylinder constructions as they approach said firing station operative to progressively separate the pistons and cylinder constructions as they recede from said station, and said means in this later action operative to fully separate the pistons and cylinder constructions for the admission of fuel to the latter at a place remote from said firing station.

8. In a compressor turbine, a stationary casing, a cylinder carrying element rotatably mounted in said casing, a piston element rotatably mounted in said casing, means whereby said elements must rotate as a, unit in said casing, an annular flange on said casing and forming a portion of a wall of each cylinder of said cylinder carrying element, turbine blades beyond said annular flange and secured to said cylinder carrying element, a firing station, means whereby the pistons and cylinders of the respective elements are progressively telescoped as the rotation of the elements carries the pistons and cylinders toward said firing chamber and whereby said pistons and cylinders are progressively separated as the elements carry them beyond said firing station, and ports in said annular' flange in its portion beyond said firing station for impressing an ignited expanding fuel charge from the cylinders on said turbine blades.

9. In a compressor turbine, a stationary casing, a first element rotatably mounted in said casing and having means at its outer periphery for cooperation with the casing to define a plurality of cylinders movable with the element as the latter is rotated, a second element rotatively mounted in said casing and at its outer periphery carrying a plurality of pistons for cooperation with said cylinders, means gearing said elements together for rotation as a unit, an annular flange on said casing and defining a portion of a wall of each of said cylinders, turbine blades at the outer side of said flange and fast to one of said elements, a firing station, means whereby the respective pistons and cylinders of the elements are telescoped at said station and separate beyond said station as said elements rotate, and ports in said flange beyond said station and through which the ignited expanding products of combustion may escape from the cylinders and impinge on said turbine blades.

10. In a compressor turbine, a rotary means, turbine blades on said means, said means comprising a pair of elements, means mounting said elements in angularly related planes for rotation together and for a relative rocking movement, impellers on and movable with said means to compress a fuel charge by centrifugal action, piston and cylinder constructions on said means to thereafter further compress said fuel charge by a positive mechanical compression, means to fire said charge, and means whereby the expanding ignited products of combustion are impressed on said turbine blades.

11. In a compressor turbine, a, rotary multicylinder construction and a rotary multi-piston construction, means positively connecting turbine baldes to one of said constructions, means for compressing fuel by centrifugal action and supplying it to the cylinders of said multis cylinder construction and thereafter mechanically compressing it by telescoping of the respective cylinders and pistons of said constructions, means for firing the charges in the respective cylinders while the cylinders and pistons are telescoped at a predetermined place in the path of rotation of the constructions, and means for conducting the expanding products of combustion Irom said cylinders to said blades.

12. In a compressor turbine, a rotary multicylinder construction and a rotary multi-piston construction, means positively connecting turbine blades to one of said constructions, means for compressing fuel by centrifugal action and supplying it to' the cylinders of said multicylinder construction and thereafter mechanically compressing it by telescoping of the respective cylinders and pistons of said constructions, means for firing the charges in the respective cylinders while the cylinders and pistons are telescoped at a predetermined place in the path of rotation of the constructions ports for conducting the expanding products of combustion from said cylinders to said blades, and said second mentioned means thereafter operative to progressively separate said cylinders and pistons as they move by said ports and to finally separate them beyond said ports.

13. In a compressor turbine, a stationary casing, a first element rotatably mounted in said casing and having means at its outer periphery for cooperation with the casing to define a plurality of cylinders movable with the element as the latter is rotated, a second element rotatively mounted in said casing and at its outer periphery carrying a plurality of pistons for cooperation with said cylinders, means connecting said elements together'for rotation as a unit, an annular fiange on said casing and defining a portion of a wall of each of said cylinders, turbine blades at the outer side of said flange and fast,

to one of said elements, a firing station, means whereby the respective pistons and cylinders of the elements are telescoped at said station and separate beyond said station as said elements rotate, and ports in said flange beyond said station and through which the ignited expanding products of combustion may escape from the cylinders and impinge on said turbine blades.

14. In a compressor turbine, a rotary multicylinder construction and a rotary multi-piston construction, turbine blades rotatable with one of said construction, means for compressing fuel by centrifugal action and supplying it to the cylinders of said multi-cylinder construction and thereafter mechanically compressing it by telescoping of the respective cylinders and pistons of said constructions, means for firing the charges in the respective cylinders while the cylinders and pistons are telescoped at a predetermined place in the path of rotation of the elements, and means for conducting the expanding products of combustion from said cylinders to said blades.

15. In a compressor turbine, a rotary multicylinder construction and a rotary multi-piston construction, turbine blades rotatable with said constructions, means including impeller blades carried by opposing faces of said constructions for compressing fuel by centrifugal action and supplying it to the cylinders of said multi-cylinder construction, means for thereafter telescoping the cylinder and pistons of said constructions to mechanically compress the fuel in said cylinders, means for firing the charges in the respective cylinders while the cylinders and pistons are telescoped and at a predetermined place in the path of rotation of the elements, and means for directing the expanding products of combustion from the cylinders to said turbine blades.

16. In a compressor turbine, a rotary multicylinder construction and a rotary multi-piston construction, turbineblades rotatable with said constructions, means including impeller blades ca ried by one of said constructions ior comconstruction, means positively connecting turbine blades to one of said constructions, means for compressing fuel by centrifugal action and supplying it to the cylinders of said multi-cylinder constructions, one of said constructions arranged at an angle to the other whereby for, a portion of a revolution the cylinders and pistons are moving into telescoping relation and for the other portion they are separating whereby during the first mentioned portion of the revolution said fuel in the respective cylinders is being com;- pressed, means for firing the charges in the respective cylinders approximately at the end of the first mentioned portion of the revolution 01' the constructions, and means for directing the expanding products of combustion from the cylinders to the blades.

18. In a compressor turbine, a pair of members, means mounting said members for rotation together and for relative lateral movements, means rotatable by one of said members to compress a fuel charge by centrifugal action, means for further compressing said fuel charge by p itive mechanical compression on relative lateral movements of said members, turbine blades in positive driving relation with one of said members, means for igniting said fuel charge following compression thereof on said relative lateral movements of said members, and means for impressing the ignited charge on said turbine blades.

19. In a compressor turbine, a pair of means ro- 12 tatable as a unit and of which one is movable toward and from the other while both are rotating, means for supp s a combustible charge to saidpair of means, impellers rotatable with said pair of means to compress said charge by centrifugal action as the means of said pair rotate, other means to further compress said charge by mechanical action as said one means i of said pair moves toward the other thereof, a

rotatable element carrying turbine blades, an igniter for the compressed charge, and means for impressing the ignited charge on said turbine blades to impart rotation to said element.

20. In a compressor turbine, a pair of means rotatable as a unit and of which one is movable toward and from the other while both are rotating, means for supplying a combustible charge to said pair of means, impellers rotatable with said pair of means to compress said charge by centrifugal action as the means of said pair rotate, other means to further compress said charge by mechanical action as said one means of said pair moves toward the other thereof, a rotatable element carrying turbine blades, an igniter for the compressed charge, means for impressing the ignited charge on said turbine blades to impart rotation to said element, and said element rigid with one of the means of said pair of means whereby as said element is rotated by said ignited charge it causes rotation of said pair of means.

JOSEPH YOUHOUSE.

REFERENCES CITED The following references are of record in the file of this patent:

UNITED STATES PATENTS

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