US2927426A - Jet turbines - Google Patents

Description

March 8, 1960 J. WELSH 2,927,426

JET TURBINEs Filed May 15, 1957 4 sheets-sheet 1 L. J. WELSH JET TURBINES March 8, 1960 4 Sheets-Sheet 2 Filed May 15, 1957 L. J. WELSH JET TURBINES March 8, 1960 4 Sheets-Sheet 3 Filed May l5, 1957 INVENTOR. laila@ J W/z, BY rm '/m WMM March 8, 1960 L. J. WELSH 2,927,426

JET TURBINES Filed May 15, 1957 4 Sheets-Sheet 4 INVENTOR.

United States The present invention is directed to a new and improved jet turbine in the form of a motor particularly adapted as a power source for the operation of vehicles such as automobiles and tractors.

It is an object of the present invention to provide a new and improved jet turbine of uncomplicated lightweight structure capable of developing a substantial amount of power as a result of improved efciency of operation, the net available power provided being' iucreased over that available from avconventional. piston type motor of' equal power size, the jet lturbine being of a relatively small size and capable of highly eicient long life operation.

A further object is to provide a new and improved jet turbine motor which essentially eliminates the use of relatively moving parts and thus substantially eliminating the need of lubrication in operation, the operational structural features of the motor affording advantageous use of centrifugal thrust to greatlyincrease efciency of operation, the motor furtherbeing provided with a muffler or exhaust silencing arrangement whereby the long life efficient operation of the same is materially enhanced.

Still a further object taken in conjunction with the foregoing is to provide a new and improved turbojet engine consisting essentially of a rotatable wheel provided with an air intake zone located radially inwardly of an air compression zone which is in communication with a combustion zone from which combustion gases are delivered into a gas expansion and exhaust zone located about the outer perimeter of the wheel, the arrangement of the zones and the structural features of the elements defining the same providing for advantageous use of centrifugal thrust in greatly enhancing the efficiency of operation of the engine.

Other objects not specifically set forth will become apparent from the following detailed description made in conjunction with the drawings wherein:

Fig. l is a fragmentary section in elevation of the jet turbine of the present invention illustrating the operative mounting of the same relative to a drive shaft;

Fig. 2 is a fragmentary, partly sectioned top plan view of the turbine wheel;

Fig. 3 is an enlarged fragmentary section erally along line 3-3 of Fig. 2;

Fig. 4 is an enlarged fragmentary plan view of the turbine wheel having portions thereof in section to illustrate operation of the wheel;

Fig. 5 is an enlarged fragmentary section taken generally along line 5-5 of Fig. 4;

Fig. 6 is a bottom plan view on reduced scale of the turbine wheel illustrating the exhaust silencing assembly mounted relative thereto and forming a part of the present invention;

Fig. 7 is an enlarged fragmentary section taken generally along line 7-7 of Fig. 6;

Fig. 8 is an enlarged fragmentary section taken generally along line 8--8 of Fig. 6; and

taken gen- Fig. 9 is a fragmentary section in elevation of a modiied form of fuel delivery arrangement for use in the engine assembly of Fig. l.

Referring to Fig. l a reduction gear box 15 of known type is illustrated as including a drive shaft 16 extending therethrough and suitably journalled by roller bearings 17. Within the box 15 the shaft 16 carries a large bevel gear 18 suitably keyed thereto and meshed at the top thereof with an input bevel gear 19 provided with an upwardly extending, integral collar or sleeve 20 having a conical central opening therethrough which is wedgingly engaged on the lower conical end portion of an input spindle or shaft 21 and held thereon byA a nut 22. The integral structure including the gear 19 and collar 20 is suitably keyed to the shaft 21 and journalled in the top portion of the gearbox 15 by roller-bearings 23. The shaft 21 is rotated by the new and improved turbine wheel 24 of the present invention to drive the output shaft 16 through the reduction gear arrangement within the gear box 15. The particular installation disclosed is especially adapted for use in vehicles such as automobiles and tractors and is merely illustrative of one manner of use of the turbine wheel 24 of the present invention. p A

The top end portion of the input shaft 21 is hollowedout to provide centrally inwardly thereof a fuel delivery chamber 25 having in communication therewith an intake pipe or valve 26 which is movably received through a collar or sleeve 27 threaded into the uppermost end of the shaft 21. An oil chamber 28 is attached with the upper end of the shaft 21 by the collar 27 and is closed at the top thereof with a threaded plug 29 being centrally apertured and receiving therethrough the intake tube 26. The bottom end of the tube 26 is provided wit-h a radial flange 30 which is seated against the' bottom edge of the sleeve 27 and resiliently held in this position by a coil spring 31 received about the tube 26 outwardly of the oil chamber 23. A holding nut 32 is threadedly received on the uppermost end of the intake tube-26 to provide a seat for one end of the spring 31, the other end of the spring being received against the top surface of the plug 29. The spring 31 functions to hold the tube 26 out of the chamber 25 to prevent interference thereby with fuel delivery in a manner to be described.

Suitable fuel delivery means, such as copper tubing, is connected to the top end of the intake tube 26 to deliver fuel into the chamber 25 and upon rotation of the input shaft 21 by operation of the turbine wheel 24, the intake tube 26 is held stationary against rotation within the upper end of the shaft 2l while the remaining elements rotate with the shaft 21. The oil chamber 2S provides lubrication within the sleeve 27 and `the spring 31 holds the shoulder 30 in sealing engagement with the lowermost end of the collar 27 to prevent loss of lubricant into the chamber 25. The spring 31 serves an additional function which Will be subsequently described in connection with the operation of the turbine wheel24.

Referring particularly to Figs. l and 2, the turbine wheel 24 is formed from a top plate 33 and a bottom plate 34, both of which are of equal diameter and disk-like shape while being centrally apertured for mounting on the input shaft 21 in spaced relation to one another. The plates 33 and 34 are held together at the centers thereof by a spacer 35 which is shrunk-fitted onto the input shaft 21 in position to surround the fuel delivery chamberZS. The spacer 35 is additionally fixed to the shaft 21 by any suitable arrangement such as a key 36 for positive rotation of the turbine wheel 24 with the shaft. The shaft 21 and spacer 3S are provided with a plurality of vertically offset drilled ports 37 which are circumferentially ar- Y 3 i ranged and extend radially outwardly therefrom being in communication with a plurality of fuel delivery pipes or tubes 3S which at their innermost ends `are threadedly received within enlarged outer end portions of each port 37. The tubes 3S extend radially outwardly intermediate the plates 33 and 34 and are received through aligned openings in an annular -upstanding wall or ring 39 extending vertically between the inner surfaces of the plates 33 and V34 and suitably attached thereto. The wall 39 defines the inner perimeter of an air intake chamber or zone 453y which is circumferentially continuous and positioned near the outer perimeter of the wheel 24.

The air intake yzone V'40 is subdivided by a horizontally directed baie plate or ring 4?. which is suitably attached to the outermost Surface of the wall 39 and extends radially outwardly into outer end engagement with a plurality of circumferentially arranged compressor blades or iins 42. Both the top plate 33 and bottom plate 34 are provided with a ring of rectangularly shaped openings 43 which are circumferentially spaced 'and in communication with a plurality of' air scoops 44. As particularly shown in Figs. -2 and 3., the air scoops 44 are each defined by upstanding side walls 4S and a rearwardly inclined top wall 46. The scoops 44 open in the direction of rotation of the wheel 24 and the forward edges of the side walls 45 and top walls 46 are bevelled to provide for reduced air flow resistance. Similarly, the forward edges of the openings 43 are bevelled to eliminate 'sharp edges for contact by air flow.

As particularly shown in Fig. 2, the compressor blades 42 are radially inclined so that'th'eir outer ends are directed away frornthe direction of rotation 'of the 'wheel 24. Still further, the outer vertical edge of each blade 42 is sharpened by bevelled surfaces to provide for reduced air ow resistance of the type previously described in connection with ythe bevelled edges of the air scoops 44. The 'ring of spaced compressor blades 42 defines the inner perimeter of a circumferentially continuous combustion lz'o'ne o`r 'chamber 47 having in 'communication therewith the outermost ends of the fuel delivery tubes 38. The outer end portion 48 of each tube 38 is inclined in a direction away from the direction of rotation of the wheel 24 and extends between spaced compressor blades 42 in substantially parallel relation therewith. ln this manner air is picked up by the scoops 44, delivered into the air chamber 40, compressed by the blades 42, delivered into the combustion zone 47 and mixed therein with fuel delivered into the combustion zone 47 by the tubes 3S.

Referring to Fig. l, the bottom plate 34 has mounted therethrough 'oppositely positioned spark plugs 49 the vrinnermost vends of which are in communication with the combustion Zone 47. The top portion of the gear box 15 in which the input shaft 21 is journalled carries a radially directed arm 5d provided at the end thereof with an electrode plate S1 having connected thereto the negative lead 52 of any suitable ignition system. The 'electrode plate 51 is positioned by the arm 59 in spaced relation to the negative electrode of the plugs 49 at approximately 1/16 of an inch to provide for energization of Veach spar-k plug 49 upon rotation of the wheel 24 to initiate combustion in the combustion chamber 47. Any suitable starter system such as a starter motor of the type in conventional use in automobiles can be used to initially'rotate the drive shaft 16 and thus turn the wheel 24 until one of 'the plugs 49 is energized by arcing between the negative electrode thereof and the electrode plate 5i to' a plurality of circumferentially arranged, tortuous passageways 54 into which the combustion gases are delivered for expansion and exhausting outwardly of the wheel 24 to rotate the same in reaction type operation. Each of the exhaust flutes 53 is defined by an upstanding inner wall segment 55 integrally joined with an outer upstanding wall segment 56 having received therebetween in spaced parallel relation a wall segment 57 forming a part of an adjacent exhaust ute 53. The wall segment 57 extends in the direction of rotation of the wheel 24 and defines with the inner free end of the wall segment 55 an inlet port or opening 5S through which combustion gases are introduced into the passageway 54. The wall segment 57 further defines with the free end of the wall segment 56 an outlet passageway or port 59 through which the combustion gases following expansion are exhausted from the wheel 24 to provide the power necessary to operate the same.

All of the 'elements described which form the wheel 24 are lixe'd relative to one another for rotation with the wheel 24, and as a result, 'there are no moving parts provided which must be lubricated to prevent undue frictional wear. All of the elements are welded in position to provide 'for a lstrong wheel structure capable of exceptionally high rotational speeds. One preferred form of interconnecting the vertically directed elements, such as the compressor blade 42 and 'the wall segments of the exhaust flutes Sbetween the plates 33 yand 34, is shown in Fig. 5. The wall segment 55 shown therein is provided with spaced upwardly and downwardly projecting V-shaped ribs 6 which are received in apertures 61 carried by 'the plates 33 and 34, the spaces between the edges of the apertures 6l and the edges of the ribs 60 being filled by weld to flxedly hold the Wall segment 55 in its operative position. In this manner a'strong unitary structure -is provided.

In operation of the turbine wheel 24 las particularly shown in Fig. 4, vcombustion vis initiated in the combustion zone 47 by the `spark plugs 49 and upon rotation of the wheel 24 air is delivered Iinto the air chamber 4i) through the scoops 44. This action forces air between the compressor blades 42 wherein the air is compressed and introduced into the 'combustion chamber 47. The wall 39 prevents air from being delivered radially iuwardly between the plates .33 and 34 and the baffle ring 41 provides for better control lof air flow toward the compressor blad 42. By subdividing the air chamber 4t) with the baffle vring 41, air confusion does not result and 'a quicker v'and 'more direct air route is provided for 'delivering air .into the compressor blades. vFuel is delivered through :the tubes 38 -in'tc the combustion chantber 47 and mixed with the compressed air therein for ignition purposes. The fuel lines-or tubes 38 are circumferentially offset in an alternating manner for wheel balancing purposes and a suliicient number of tubes 33 will be preferably lused to provide one fuel line for each pair of exhaust -liutes S3. For greatest yoperzttional eiiiciency however, a single fuel `line may be provided for each separate exhaust fiiute but from an Aecenorrlical standpoint it has been found that highlyeliicient-operation can be obtained by merel-y'providing a singlefuel Aline for each pair of exhaust flutes.

Fuel is delivered through .the intake valve Lor tube 26 into the delivery chamber 25 'from Whicl1=itmcveseut wardly through 'the tubes 33. The'tube 26 is spring mounted to hold the same in lpiace 'and to lprevent leakage of fuel and oil. This vis ynecessary particularly when the jet turbine motor -is shut `oif following operation. A strong vacuum is formed 'in -the A'fuel delivery chamber 25 and tends to pull the "deliverytube 2`6'downwardty into the 'chamber 25. The spring Y'31 functions to prevent displacement of the Atube '26 which will result oil leakage from the oii chamber 28. The combustion gases formed in the combustion :chamber -4'7 moves Athrough the passageways or ports 58 into the passageways 54- of the exhaust flutes 53 and during'tlieirtravel therein expansion takes place to provide for exhausting of the same from the ports S9 at a greatly increased velocity for high speed operation of the wheel 24.

The structural arrangement of the wheel 24 of the present invention is of particular importance in that it provides for advantageous use of centrifugal thrust which occurs during rotation of a disk or wheel about an axis. The centrifugal thrust developed provides additional power which is advantageously used by the turbine wheel of the present invention to increase the eciency of operation of the same in several respects. Centrifugal thrust will aid in fuel delivery through the tubes 38, air delivery to the compressor blades 42, and maintaining of pressure diiferential within the combustion chamber 47 which enhances efficient utilization of the combustion gases by the exhaust flutes 53. The centrifugal thrust advantageously used during operation of the wheel 24 of the present invention increases with an increase in rotational speed of the wheel. With the added action of centrifugal thrust on the combustion gases in the combustion chamber 47, the combustion pressure against the exhaust utes 53 is greatly increased and is substantially greater than the back pressure developed by combustion against the compressor blades 42. This increase in pressure differential within the combustion zone 47 can, for example, establish an outwardly directed total thrust which may be 35% greater than the back pressure operating in a direction toward the compressor blades. If the turbine is operated at a speed of approximately 25,000 rpm., the combustion pressure against the exhaust flutes 53 may be as much as 35% greater than the back pressure against the compressor blades 42 to provide for greatly increased power supplying pressure diiferential within the combustion chamber 47.- The air scoops and compressor blades are located well within the radius of location of the exhaust fiutes to further make full use of centrifugal thrust in increasing the ow of air outwardly through the air chamber and compressor blades into the combustion zone. With the structural arrangement described, centrifugal force is harnessed and utilized to provide for a substantial increase in power of operation without any increase in cost of operation. 'I'he net power output of the turbine motor of the present invention may be as much as or more than 60% utilization of power input thereby providing substantial savings of power both from the standpoint of economy of operation and efficiency of operation. Economy of operation arises from full utilization of centrifugal thrust whereas eiciency of operation arises from the elimination of moving parts requiring lubrication and increasing loss of efficiency due to development of friction.

The exhaust utes 53 are shaped to make more eiiicient use of the expanding combustion gases traveling through the passageways 54 therein. While providing for eicient expansion of the combustion gases, the passageways 54 are nevertheless capable of maintaining sufticient resistance at the outlet or exhaust ports 59 to maintain the necessary high compression within the combustion zone 47. The number of exhaust flutes 53 used will depend upon the particular use of the motor. For best efiiciency, as many as 16 utes can be used in a turbine wheel of approximately 18 inches in diameter. Such an arrangement permits more than 3 inches of travel distance for the combustion gases within the passageways 54 to fully utilize expansion of the combustion gases and permit these gases to reach their fullest and fastest speeds upon exhausting through the ports 59. With this arrangement, the most eicient and powerful thrust or reaction results thus providing for high speed operation of the turbine wheel.

To provide the necessary length of combustion gas travel in the exhaust utes, the inner wall segments 55 may be made longer than the outer wall segments 56 as illustrated. This arrangement spaces the exhaust ports 59 substantially away from the adjacent shoulder formed by the integral juncture of the wall segments 55 and 56 of an adjacent exhaust ute 53 to prevent undue damage by heating caused by direct discharge of the exhaust from a port 59 onto the adjacent shoulder.

Referring particularly to Figs. 6-8, a preferred form of exhaust control muffler or silencer 62 is illustrated. The silencer is of two-piece construction leach portion being semi-circular for positioning about the outer perimeter of the wheel 24. Each section as shown in Fig. 7 includes an outer vertical wall 63 to which is suitably attached horizontally inwardly directed top and bottom walls 64 and 65 respectively. The walls 64 and 65 are adequately spaced from one another to be received inwardly of the outer perimeter of the Wheel 24 in spaced relation outwardly of the plates 33 and 34. Each silencer section is provided with an enlarged portion 66 having a downwardly directed sleeve 67 attached to the bottom wall 65 thereof in register with an opening 68 therein. The sleeve 67 is adapted for attachment with an exhaust pipe of known type to deliver exhaust from the silencer segment to the rear of the vehicle.

The inner ends of one of the segments as particularly shown in Fig. 8 are each provided with a sleeve 69 suitably riveted thereto which telescopically receives therein the adjacent free end of the remaining silencer segment to interconnect the same about the wheel 24. A friction t may be utilized to hold the segments in interconnected relation or removable fastening means may be used if preferred. In this manner the separate silencer segments are received about the outer portion of the wheel 24 and are suitabily mounted in xed relation relative to the wheel 24 to allow the wheel to rotate relative to the silencer 62 without contacting any part of the same while at the same time delivering exhaust combustion gases thereinto for controlled venting thereby.

As particularly shown in Figs. 6 and 7, the outer edge of each of the plates 33 and 34 carries a radially directed rim which is subdivided into a pluralityof upwardly or downwardly directed tooth-like ribs 70. The ribs 70 are circumferentially spaced and define a substantially U-shaped groove therebetween the bottom surface 71 of which is bevelled to provide an upward inclination in an outward direction. The bevel is approximately 45 relative to the horizontal and provides for a plurality of controlled intake ports about the outer perimeter of the wheel 24 whereby air is drawn into the silencer 62 to provide cushions of air moving along the inner surfaces of the top and bottom walls 64 and 65 respectively to further silence the discharge of the exhaust gases into the mufer 62. The bevelled bottom surfaces 71 provide for controlled direction of air drawn in response to centrifugal actio-n into the silencer 62 and these currents of air move substantially horizontally across the inner surfaces of thetop and bottom walls of the silencer. Insuiiicient air is centrifugally drawn into the silencer to interfere with the operational eiciency of the wheel 24 but the amount of air which is introduced provides an air seal preventing escape of sound waves and providing efficient sound deadening action. 'Ihe air cushions provided press out against the walls o-f the muier to cushion the same against the thrust of the exhaust gases and this air cushion is automatically provided by centrifugal action arising from operation of the turbine wheel 24. Thus, no additional power is utilized nor special operational structures provided for the provision of the exhaust silencing air currents.

The introduction of air through the grooves dened by the ribs 70 into the silencer 62 provides still a further important function enhancing efficiency of operation of the turbine wheel 24. The drawing of the vair currents across the outer surfaces of the plates 33 and 34 in close proximity to the combustion zone 47 and the gas expansion and exhaust zones 'defined by the flutes 53 functions to cool the structural elements of the wheel 24 and increase the operational life of the same.

In Fig. 9 a slightly modified form of .fuel delivery arrangement is illustrated for use in the installation of Fig. l. The intake tube 26 carries a threadedly held collar '72 thereon interiorly of the oil chamber 28, the collar seating the upper end of a coil spring 73 which is seated at its lower end against the upper end of the sleeve ,27. The spring 73 is tensioned to constantly urge the tube 26 in an upward direction to hold the bottom rib 30 thereof against movement downwardly into the fuel delivery chamber 25. As previously described, it is necessary for the tube 26 to remain stationary during rotation of the input shaft 21 and the elements carried therebyand in using this arrangement it becomes necessary to hold the tube 26 out of the fuel delivery chamber 25 when the motor is turned off following operation as a result of a vacuumbeing developed in the chamber 25' which tends to draw the tube 26 downwardly thereinto. Any suitable arrangement can be used, the two arrangements shown in Figs. l and 9 having been found entirely adequate for the purposes described.

Any suitable fuel can be used in the operation of the turbine motor of the present invention. Bottled gas has been found to be perfectly adequate and actually preferred due to the elimination of a carburetor or force pump for positive delivery of the fuel to the chamber 25 in the input shaft 21. The pressure carried by the tank containing the gas in addition to the action of eentrifugal thrust on the delivery of the gas through the tubes 38 provides for adequate combined delivery forces. By advantageously utilizing centrifugal thrust, the combustion zone or chamber 47 may be unusually small in area. The centrifugal thrust materially increases gas pressure in the exhaust flute portion of the wheel to establish the requisite pressure differential on either side of the combustion chamber 47 as previously described. The centrifugal thrust will increase with increased speed of operation of the wheel thus allowing high speed operation Without loss of economical fuel consumption.

The turbine motor of the present invention is intended primarily for use in automobiles and tractors although, due to its versatility, it can be readily converted to substantially any use made of a regular piston type engine. The turbojet motor described is combined in an automa bile for use with a conventional form of transmission and clutch as well as starter motor in the manner previously described. Upon starting, there is no engine warming time necessary as the jet motor immediately upon attaining self-sustaining combustion is ready for load application. A jet turbine motor of 150 Hl. can be manufactured with a total weight of slightly less than 80 pounds, a height of from 8 to 10 inches and a width or diameter of 18 inches. The gauge of the metal used in fabricating the exhaust flutes and compressor blades can be much greater than conventionally practiced for increased life of operation as the additional weight added thereby is of no consequence. The motor will start at approximately 3,500to 4,000 rpm., idle at approximately 5,000 r.p.m. and reach a top speed which can possibly be as high as 50,000 rpm. providing the material from whichthe motor is fabricated is of sufficient strength capable of withstanding the centrifugal thrust developed.V The `exhaust pressure in the combustion chamber varies with opening and closing of the throttle andthe response is instantaneous thus providing for smooth uninterrupted operation. The size of motor described includes a combustion chamber which utilizes less than 25% of the total area of the wheel and, as a result, the motor will operate at substantially normal temperatures. The flow of cool air across the outer surfaces of the wheel into the exhaust silencing assembly further maintains the operational tem-- perature of the motor at a minimum While additionally materially silencing the exhaust to an extent that quiet operation can be readily attained.

Obviously many modifications and variations of the invention as hereinbefore set forth may be made without departing from the spirit and scope thereof, and therefore only such limitations should be imposed as are indicated in the appended claims.

I claim:

l. A jet turbine assembly including a turbine wheel lixedly mounted on a shaft to rotatably drive the same, fuel delivery means forming a part of said shaft and deiining a fuel delivery chamber therein, said wheel surrounding said shaft in close association with said chamber and being dened by spaced top and bottom plates, an annular wall extending between said plates and having Aextending ltherethrough the outer end portions of a plurality of radially directed fuel dispensing tubes the inner ends of which are in communication with said chamber, theouter surfaces of said plates carrying a plurality of cup-.like air scoops in ring-like arrangement and in com-` munication with circumferentially spaced openings in said plates located immediately outwardly of said wall, said scoops opening in the direction of rotation of said wheel,

a radially extending circumferentially'continuous baffle carried by the outer surface of said Wall intermediate said plates and receiving said tubes alternately above and below the same, a plurality of compressor blades circumferentially arranged immediately outwardly of said baffle and extending between said plates, said blades each being radially outwardly inclined away from the direction of rotation of said wheel, and a plurality of overlapping ex haust flute elements circumferentially carried between said plates near the outer perimeter of said Wheel in radially spaced relation to said blades to define therebetween a combustion zone, said flute elements defining therebetween a plurality of substantially U-shaped combustion gas expansion passageways the outermost ends of which are exhaust ports through which gas escapes to impart rotational movement to said wheel.

2. A jet turbine assembly including a turbine wheel fixedly mounted on a shaft to rotatably drive the same, fuel delivery means forming a part of said shaft and defining a fuel delivery chamber therein, said wheel surrounding said shaft in close association with said chamber and being defined by spaced top and bottom plates, an annular wall extending between said plates and having rality of radially directed fuel dispensing tubes the inner ends of which are in communication with said chamber,

the outer surfaces of said plates carrying a plurality of cup-like air Scoops in ring-like arrangement and in communication with circumferentially spaced openings in said plates located immediately outwardly of said wall, said scoops opening in the direction of rotation of said wheel, a radially extending circumferentially continuous baille carried by the outer surface of said wall intermediate said plates and receiving said tubes alternately above and below the same, a plurality of compressor blades circumferentially arranged immediately outwardly of said baiiie and extending between said plates, said blades each being radially outwardly inclined away from the direction of rotation of said wheel, a plurality of overlapping exhaust iiute elements circumferentially carried between said plates near the outer perimeter of said wheel in radially spaced relation to said blades to dene therebetween a combustion Zone, said flute elements defining therebetween a piurality of substantially U-shaped combustion gas expansion passageways the outermost ends of which are exhaust ports through which gas escapes to impart rotational movement to said wheel, and a circumferential sieeve-like exhaust control and silencing member received about the outer periphery of said wheel overlapping said plates and fixed against rotation therewith, said silencing member including an exhaust outlet.

j3. A jet turbine assembly including la turbine wheel iixedly mounted on a shaft to rotatably drive theusame, fuel delivery means forming a part of said shaft and desesame ning a fuel delivery chamber therein, said wheel surrounding said shaft in close association with said chamber and being dened by spaced top and bottom plates, an annular wall extending between said plates and having extending therethrough the outer end portions of a plurality of radially directed fuel dispensing tubes the inner ends of which are in communication with said chamber, the outer surfaces of said plates carrying a plurality of cup-like air scoops in ring-like arrangement and in communication with circumferentially spaced openings in said plates located immediately outwardly of said wall, said scoops opening in the direction of rotation of said wheel, a radially extending circumferentially continuous bafe carried by the outerv surface of said wall intermediate said plates and receiving said tubes alternately above and below the same, a plurality of compressor blades circumferentially arranged immediately outwardly of said baille and extending between said plates, said blades each being radially outwardy inclined away from the direction of rotation of said wheel, a plurality of overlapping exhaust ilute elements circumferentially carried between said plates near the outer perimeter of said wheel in radially spaced relation to said blades to define therebetween a combustion zone, said flute elements defining therebetween a plurality of substantially U-shaped combustion gas expansion passageways the outermost ends of which are exhaust ports through which gas escapes toA impart rotational movement to said wheel, and a circumferential sleeve-like exhaust control and silencing member received about the outer periphery of said wheel overlapping said plates and fixed against rotation therewith, said silencing member being provided with at least one outlet for exhaust pipe connection and being sectionalized in telescopically assembled relation about said wheel.

4. A jet turbine assembly including a turbine wheel fixedly mounted on a shaft to rotatably drive the same, fuel delivery means forming a part of said shaft and defining a fuel delivery chamber therein, said wheel surrounding said shaft in close association with said chamber and being defined by spaced top and bottom plates, an annular wall extending between said plates and having extending therethrough the outer end portions of a plurality of radially directed fuel dispensing tubes the inner ends of which are in communication with said chamber, the outer surfaces of said plates carrying a plurality of cup-like air scoops in ring-like arrangement and in communication with circumferentially spaced openings in said plates located immediately outwardly of said wall, said scoops opening in the direction of rotation of said wheel, a radially extending circumferentially continuous bafe carried by the outer surface of said wall intermediate said plates and receiving said tubes alternately above and below the same, a plurality of compressor blades circumferentially arranged immediately outwardly of said baie and extending between said plates, said blades each being radially outwardly inclined away from the direction of rotation of said wheel, a plurality of overlapping exhaust flute elements circumferentially carried between said plates near the outer perimeter of said wheel in radially spaced relation to said blades to define therebetween a combustion zone, said ute elements defining therebetween a plurality of substantially U-shaped combustion gas expansion passageways the outermost ends of which are exhaust ports through which gas escapes to impart rotational movement to said wheel, and a circumferential sleeve-like exhaust control and silencing member received about the outer periphery of said wheel overlapping said plate and fLxed against rotation therewith, said silencing member being provided with at least one outlet for exhaust pipe connection and being sectionalized in telescopically assembled relation about said wheel, the outer surface at the outer edge of each plate being provided with radially directed tooth-like projections positioned within said silencing member and providing for centrifugal air l'IO . 10 currents within said silencing member along surfaces of the walls thereof.

5. A jet turbine assembly including a turbine wheel xedly mounted on a shaft to rotatably drive the same, said shaft being provided with a hollow end portion deiining at the innermost end thereof a fuel delivery chamber, a sleeve bearing fixedly received within said hollow the inner end portion in communication with said chamber, a fuel intake tube received within said sleeve and held against rotation with said shaft and movement into said chamber, said wheel surrounding said shaft in close association with said chamber and being defined by spaced top and bottom plates, an annular wall extending between said plates and having extending therethrough the outer end portions of a plurality of radially directed fuel dispensing tubes the inner ends of which are in communication with said chamber, the outer surfaces of said plates carrying a plurality of cup-like air scoops in ring-like arrangement and in communication with circumferentially spaced openings in said plates located immediately outwardly of said wall, said scoops opening in the direction of rotation of said wheel, a radially extending circumferentially continuous baie carried by the outer surface of said wall intermediate said plates and receiving said tubes alternately above and below the same, a plurality of compressor blades circumferentially arrangedimmediately outwardly of said bafe and extending between said plates, said blades each being radially outwardly inclined away from the direction of rotation of said wheel, and a plurality of overlapping exhaust ute elements circumferentially carried between said plates near the outer perimeter of said wheel in radially spaced relation to Said blades to dene therebetween a combustion zone, said flute elements defining therebetween a plurality of substantially U-shaped combustion gas expansion passageways the outermost ends of which are exhaust ports through which gas ,escapes to impart rotational movement to said wheel.

6. A jet turbine assembly including a turbine wheel fixedly mounted on a shaft to rotatably drive the same, said shaft being provided with a hollow end portion dening at the innermost end thereof a fuel delivery chamber, a sleeve bearing fxedly received within said hollow end portion in communication with said chamber, a fuel intake tube received within said sleeve and held against rotation with said shaft and movement into said chamber, said wheel surrounding said shaft in close association with said chamber and being defined by spaced top and bottom plates, an annular wall extending between said plates and having extending therethrough the outer end portions of a plurality of radially directed fuel dispensing tubes the inner ends of which are in communication with said chamber, the outer surfaces of said plates carrying a plurality of cup-like air scoops in ring-like arrangement and in communication with circumferentially spaced openings in said plates located immediately outwardly of said wall, said scoops opening in the direction of rotation of said wheel, a radially extending circumferentially continuous bale carried by the outer surface of said wall intermediate said plates and receiving said tubes alternately above and below the same, a plurality of compressor blades circumferentially arranged immediately outwardly of said baie and extending between said plates, said blades each being radially outwardly inclined away from the direction of rotation of said wheel, the outermost ends of said tubes being received between adjacent blades and being inclined in substantially parallel relation therewith, and a plurality of overlapping exhaust flute elements circumferentially carried between said plates near the outer perimeter of said wheel in radially spaced relation to said blades to define therebetween a'combustion zone, said flute elements defining therebetween a plurality of substantially U-shaped combustion gas expansion passageways the outermost ends of which are exhaust ports 11 12 through whchg'as escapes to impart rotational movment 1,945,608 Hill ..f Feb. 6, 1934 to said wheel. 2,003,500 Corless June 4, 1935 o 27,188,128 Armstrong Ian. 23, 1940 References Citaal ill the l Of this paient 2,448,972 Gi'zara Sept. 7, 1948 UNITED STATES PATENTS 5 FOREIGN PATENTS D d M 7, 1912 Y 1025251 esmoun ay 702?150 Germany Jan. 31, 1941 1,210,831 Pfeiffer Jan. 2, 1917

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