US1583159A - Gas engine of the turbine type - Google Patents

Description

May 4 1926.

1,583,159 a, P. JOYCE GAS ENGINE OF THE TURBINE TYPE Fil ed June 6, 1922 INJ- PATENT BRYANP. JOYCE, OF WASHINGTON, DISTRICT OF COLUMBIA.

GAS ENGINE OF THE TURBINE TYPE.

Application filed June 6, 1922. Serial No. 566,383.

To all whom it may concern.-

Be it known that I, BRYAN P. Joron, citizen of the United States, residing at Vashington, District of Columbia, have invented new and useful Improvements in Gas Engines of the Turbine Type, of which the following is a specification.

The subject of this invention is a gas engine of the turbine type. p I

The main objects of the invention are, the provision of a simple and efiicient turbine engine; and the provision .of means for properly compressing the charge before explosion thereof in such a way that the force of thecxplosion will act only on the rotor and will not affect the element used for compressing the charge.

-With these and other objects in View, which Will hereinafter more fully appear, my invention consists in the novel arrangement and combination of parts and in the details of construction hereinafter described and claimed, it being understood that changes in the precise embodiment of the invention herein disclosed may be madewithin the scope of what is claimed without departing from the spirit of the invention.

A practical embodiment of the invention is shown in the accompanying drawing by way of illustration, wherein Figure 1 is a longitudinal section of an engine constructed in accordance with my invention, parts in elevation; f

Figure 2 is a section on the line 2-2 of Figure 1;

Figure 3 is a section on the line 33 of Figure 1. I 7

'Referring' to the drawing by numerals of reference:

I provide a casing, preferably of tubular formation, having an attenuated portion 10 and a preferably integral enlarged portion 11.

Within the casing I mount a rotor having a shaft-like portion 12 formed with a. spiral groove 13 cut I therein and extending throughout practically I the entire length thereof. While I have shown and described this shaft-like portion as having a spiral groove therein it is understood that runners having grooves or vanes of suitable form may be substituted for the spiral groove without departing from the spirit of this invention. Connected to the por tion 12 and, conveniently integral therewith is an enlarged portion of the rotor housed within the portion 11 of the casing and consisting of a portion 14 which fits within the casing with a close turning fit, and a cylindrical portion 15 in which is cut a cam groove 16. a

Encircling the cylindrical portion'15, and having a close sliding fit thereon and within the portion 11of the casing, is a piston 17 which may be packed with rings 18. A pin 19 is mountedin the piston and extends into the cam groove 16 to cause reciprocation of the piston through rotation of the rotor. Means areprovided to prevent rotation of the piston; such means, as herein shown, may conveniently consist of a key 20 seated in a groove in the casing and engaging in a groove extending,longitudinally of the'piston.

Fuel may be fed to the engine through an intake pipe 21', the fuel entering to destroy the partial vacuum caused by movement rearwardly of the piston through a port 22' formed in the portion. 14 of the rotor. The charge thus supplied to the engine will be compressed on forward movement of the piston and will be forced through the same port 22 '(keeping in mind that the parts'as shown in the drawing are in the firing position and that the rotor is rotating in a clockwise direction as viewed in Figures 2 p and 3) and a bypass 24 into an explosion chamber 23 formed in the forward end of the portion 11 of the casing. The explosion chamber 23 is cut-oft from communication with the groove 13 by means of a sleeve 2 which surrounds the rotor at that po-rtio which passes through and which'is adja cent to the chamber except during the time that explosion is taking place within the chamber at which time the rear end of the groove 13' registers with a slot 26 provided in the sleeve. The sleeve may be held against rotation by means of a key 25 locatedin alining apertures formed in the casing and sleeve;

An exhaust chamber is provided at the forwardend of the portion 10 of the casing with which the exhaust ports 27 are in communication.

A suitable gear, such as the bevel gear 28 may be mounted on the extending end of the rot-or portion 11 and may be locked in place thereon by a nut 29. This gear and the portion 14 of the rotor, both abutting against the casing, will hold the rotor against rectilinear movement with respect to the casing.

Any preferred form of generator 30 and timer or distributer 31 may be connected to the rotor to supply current through a wire 32 to a spark plug 83 so that the'charge in 1: Aigas turbine, including a casing, pro.-

videdwith aninlet and anexhaust port, and with an explosion chamber, a rotor wlthln the.casing, said rotor provided with a spiral, groove and .a ,cam groove, and with a port:

adapted to alternately register with the inlet, port and the explosion chamber, a piston,

means carried by the piston and engaging the cam groove to reciprocate the piston througlr-rotatlonbt therotor, a sleeve surrounding the rotor and xtending through the explosion chamber, said sleeve provided with'a slot-{with which therear end of thespiral groove isadapted to periodically register and means for igniting acharge in the explosion chamber.-

2. A gas turbine including a casing provided with; a compression; chamber, with an inlet thereifer,-- with; an, explosion chamber,-

and with an exhaust from said explosion chamber; a rotor: within the casing, said rotor 'b8111g:plOV1(l8Cl*W1tl1 a single port adaptedfirst to establish communication be tween the, inlet and the compression chamber-and then between the-compression and explosion Y chambers, said rotor cutting; off;

communication between; the. two chambers after admission of a charge to said explosion, chamber, a pistonin said compression cham her, a connection between the piston and. go tor to reciprocate the former-through rotation of;the latter to first/draw a charge through the inlet and said single rotor port into the compression chamber and to then force the chargethrough said rotor port into theaexplosion; chamber, means for'igniting the charge in theexplosion chamberwhile the latter is cut, off from the compression chamber by the rotor, and rotor-controlled means for closing said exhaust untilv the charge is fired in said explosion chamber and for then. opening said exhaust to permit escape of the fired charge under pressure to perform work.

3. A .gas turbine including a casing provided with an intake and, exhaustport, a rotor. within the casing, means actuated by rotation of "the rotor for drawing in and compressing a charge of fuel, means including the rotor for cutting off the compressed charge from the compressing means, rotorcontrolled means for closing saidexhaust until the charge is fired and for then opening said exhaust to permit escape of the fired charge under pressure to perform work, and means for firing the charge while chamber, means carried by the rotor foradinitting the compressed charge to the ex; plosion chamber and cutting OK the, charge therein from the compressing means, rotor controlled means for closing the exhaust port until the charge is fired and for then opening said port to permit'escape ofthe fired charge. under pressure to perform, work, and meansfor firing the charge while;- cut oft from said compressingmeans;

5. Aigas turbine including a casing provided with an inlet and an exhaust port, and with. an explosion chamber, a, rotorwithin the casing, said rotor being providefd with a spiral grooveoand a'cam groove and with a port adapted to alternately register with the inlet port and ,the explosionv chamber, a piston, meanscarried bythe piston and .engaging the cam groove to reciprocate the piston through therotation of the rotor, means for closing therearend of saidfspiral groove until the charge isfiredinQ-theQexplosion chamber and forthenopeningsaid groove to permit outrushof thefired. .OhE lgQ therethrough, and means for igniting the charge in the explosion chamber.

6. A gas turbine including a casing pro vided with an inlet and an exhaust port, and with an explosion chamber, arotorw-itl e in the casing, saidv rotor; being provided with a spiral groove and a cam-groove,-and with a port adapted to alternatelyregister with the inlet port andthe explosion chamher, a piston, means carried by the piston and engaging the cam groove to reciprocate the piston through the rotation of the rotor, stationary means rotatably engaged by the rotor for closing-the rear end of said spiral groove until the charge is fired in the explosion chamber and for then opening, said groove to "permit outrush or". the fired charge therethrough, and means for igniting the charge in the explosion chamber,

7 A gas turbine comprising a cylindrical casing vprovided near one end witlra transverse partition dividing it into a relatively large compression chamberand a comparativelysmall explosion chamber, said partition being' iormed with a central opening and with an ofi-center port, a tubular extension;projeotingfrom said one end of the casingin line with said central opening a fuel inlet through the wall of said compression chamber near said partition, a rotor having an enlarged intermediate portion Within the casing in contact With the side of the partition toward said compression chamber and of a width to close said fuel inlet, said enlarged rotor portion having a peripheral port adapted first to establish communication between said inlet and said compression chamber and to later register with the aforesaid off-center port to place the compression chamber in communication With the explosion chamber; one end portion of the aforesaid rotor extending through said compression chamber While the other tral opening and is received in said tubular casing extension, a piston in said compression chamber surrounding said one end por-' tion of the rotor and connected therewith to be reciprocated thereby; said other end portion of the rotor having a spiral gas-escape groove, means controlled by rotation of said rotor for closing the inner end of said groove until the charge is fired in the explosion chamber, and means for firingthe charge.

BRYAN P. JOYCE.

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