US1174439A

US1174439A - Gas-turbine.

Info

Publication number: US1174439A
Application number: US82223914A
Authority: US
Inventors: Cyril G Pelley
Original assignee: EDWARD N ROBER; O D JONES
Current assignee: EDWARD N ROBER; O D JONES
Priority date: 1914-03-03
Filing date: 1914-03-03
Publication date: 1916-03-07
Anticipated expiration: 1933-03-07

Description

c.. G. P,ELLEY.

GAS TuRlNE. PPLICATIQN FILED MAR- 3 |914.

2 SHEETS-SHEET I.

Patented Mar. 7, 1916.

C..G. PELLEY.

GAS TURBINE. APPLICATION mp 11,111.3. 1914.

Patented- Mar. 7, 1916.

2 SHEETS-SHEET 2 uNITED STATES vPATENT oEErcE.

CYRIL PELLEY, OIF-LONG BEACH, CALIFORNIA, ASSIGNOR OF ONE-THIRD TO O. D. JONES, 0F LOS ANGELES, CALIFORNIA, AND ONE-THIRD T0 EDWARD N. ROBER, 0F

Y BROOKLYN, NEW YORK.

GAS-TURBINE.

Specification of Letters Patent.

Application led March 3, 1914, Serial No. 822,239.

To all 'whom' t may concern:

l Be it known that I, vCYRIL G. PEELEY, a, citizen of the.- United States, residing at Long Beach, in the county of Los Angeles and State of California, have invented a new and useful Gas-Turbine, of which the followingl is a specification.

My invention relates to gas turbines, and has for its principal object the provision of such a turbine which will have a few parts of simple construction.

A further object of my invention is to provide such a turbine which will be free from mechanically actuated valves and will be practically continuous in operation.

Further objects and advantages will be evident hereinafter.

Referring to the drawings, which are for illustrative purposes only: Figure 1 is a section taken on avertical plane passing through the axis of the turbine. Fig. 2 is a section on the plane :v2-m2 of Fig. 1, looking in the direction of the arrows. Fig. 3 is a section taken on the plane @o3-m3 of Fig. 1, looking in the direction of the arrows. Fig. 4 is a diagram of the connections.

The invention as illustrated consists of two series of stationary blades 2 and 3 separated by a partition 3', and two series of rotatable blades 4 and 5, the latter being mounted on a shaft 6 which also -carries a rotary compressor 7 The rotary compressor 7 furnishes air to an air pipe 8 which furnishes air under compression to a nozzle 9 which is supplied with gasolene or other liquid fuel through a pipe 10. The explosive mixture of air and gasoiene from the nozzle 9 is carried to a series of valves 11, passing through these valves into explosion chambers 12, each of which is pro vided with a spark plug 13.

Considering the structure more in detail the shaft 6 has keyed upon it a hub 14 which has formed integral with it a disk 15 to which is secured rotor members 16 and 17 by means of' bolts 18, the rotor members 16 and 17 having formed integral with them the two series of rotatable blades 4 and 5. The stationary blades 2 and 3 are formed upon a casing 19. There are also formed upon the casing 19 three flat projections 20 to which are secured valve chambers 21 in which the explosion chambers 12 are formed and into which the spark plugs 13 are secured. The pipe 8 communicates with sages a serles of gas chambers 22 each of which 1s closed at lts upper end by a plug 23 through which a valve stem 24 passes. A conical valve 25 is secured to the lower end of the valve stem 24 and seats in an openingbetween the explosion chamber l2 and the gas chamber 22, being held in the closed pos1t1on by means of a spring 26 coperatlng with a washer 27 and-a nut 28 on the valve stem 24. The casing 19 also has formed 1n 1 t by-pass passages 29, these pashavmg approximately the form shown ,1n Flg. 3 and extending entirely across the caslng as shown at 30 in Fig. l. A serles of exhaust ports 31 are also formed 1n the casing 19 adjacent to the stationary blades 3 approximately in the same angular positlon as the valves 11 which are adjacent to the stationarvblades 2.

An end plate 32 is secured to one end of the casing 19 and has a bearing 33 formed thereon for supporting the shaft 6. An end plate 34 is secured to the other end and has a bearing 35 thereon for supporting the shaft 6. A compressor housing 36'is secured to the end plate 34 and has a circular opening 37 formed therein, this opening being eccentric with the shaft 6 as shown in Fig. 2. A comp ressor center 38 is keyed to the shaft 6 inslde the opening 37 and is of sufficient width to fit tightly in said opening. A series of radial slots 39 are formed in the center 38 and wings 40, preferably of fiber or similar material, are inserted in these slots. An opening 41 is provided in open communication with the pipe 8 and an intake opening 42 is formed in open communication with the outside air in approximately the loca' tions shown in Fig. 2. The gasolene pipe 10 enters the pipe 8 through a coupling 43 and gasolene is injected into the stream of air passing through the pipe 8 by means yof the Suitable ignition means are provided as diagrammatically shown in Fig. 4, in which 45 is a magneto, 46 is a transformer consisting of a primary 47 and a secondary 48. 49

is a distributer consisting of a rotatable member 50 and a series of stationary buttons 51. The stationary buttons 51 `are connected by means of wires 52 with the spark yplugs 13 of the turbine.

distributer v49 may be continuous at a constant speed, or it maybe made intermittent, or the speed varied for the purpose of regulation.

The method of operation of the invention is as follows: The shaft (S being rotated by any convenient external means, the center 38,is rotated and the wings 4() are thrown out against the inner surface of the opening v 37 by centrifugal force. Air is drawn into the opening 37 through the opening 42, and this air is compressed and driven into the pipe S through the opening 41. This air is mixed with gasolene, or similar fuel, entering through the pipe 10, and an explosive mixture of liquid fuel and air is thereby supplied to the pipe 8. As the pipe 8 is in open communication with the 'gas chambers 22 a constant supply of explosive mixture under pressure is maintained in these chambers so long as the shaft 6 is rotated and gasolene or similar fuel is supplied to the pipe 10. Whenthis pressure rises to a sufficiently high value to open the valves 11 a supply of this explosive mixture is admitted to the explosion chambers 12. A high tension intermittent current is supplied to the spark plugs 18 through the wires 52 by means of the dis-A tributer 49, the transformer 46, and the magneto 45. This high tension intermittent current causes a series of high tension sparks to pass at intervals across the points of the spark plugs 13 and explodes the mixture in the explosion chambers 12. This explosion closes the valves 11, this closure being assisted by the springs 26 and the force of the explo-sion acts upon the series of rotating i on and blades 4 thrfugh the series of 'stationary blades 2 furnishing power to the rotating blades 4. The compressed gases are pocketed between the rotating blades 4 and are carried around by the rotation of these blades until they come under the stationary blades adjacent `to the passages 30. A further expansion takes place in these passages the hot gases moving axially of the turbine andd passing into the rotating blades 5 and through the stationary blades 3 adjacent to the passages 30. This expansion furnishes ad itional power to the rotating blades 4 and 5 and the hot gases which have expand- 'ed to a point slightly above atmospheric pressure are carried around and exhaust into the atmosphere through the exhaust openings 31.

With the form of distributer shown in the diagram the spark plugs are simultaneously energized and the explosions in the explosion chambers 12 Will also be simultaneous. This isdesirable as it equalizes the radial thrustl upon the shaft 6 and prevents undue wear strains in the turbine mechanism.

Should it be desired to obtain a more gradual rate of expansion the size of the parts may be changed and additional series of stationary and movable blades mayv be added, each series of stationary` blades exhausting into the next succeeding series, and each series of movable blades exhausting into the next series of movable blades. The drawings illustrate a two. stage turbine but these stages may be increased and in vsome cases the eliciency of the turbine will be increased by supplying additional stages.

What I claim is 1. A'gas turbine comprising a casing, a shaft turning in said casing, a rotor mounted on said shaft, a series of movable blades on the'periphery of said rotor, a series of explosion chambers in said casing, stationary blades in said casing extending inwardly and so shaped as to direct any pressure produced in said explosion chambers against said movable blades, means for producing explosions in said explosion chambers, a series of exhaustl passages in said casing, and aseries of stationary blades for directing the gases from the-movable blades through 'said exhaust passages..

2. A gas turbine comprising a casing, a shaft turning in said casing, a rotor mounted on said shaft, -a series of movable blades on the periphery of said rotor, a series of explosion chambers in said casing, stationary blades in said casing extending inwardly and so shaped as to direct any pressure produced in said explosion chambers against said movable blades, an inlet valve in each explosion chamber, means-for supplying an explosive mixture to said chambers through said valve, means for producing explosions in said explosion chambers, a series of exhaust passages in said casing, and a series of stationary blades for directing the gases from the movable blades through said exhaust passages.

3. A gas turbine comprising a casing, a shaft turning in said casing, a rotor mounted on said shaft, a series of movable blades on the periphery of said rotor, a series of explosion chambers in said casing, stationary blades in said casing extending inwardly and so shaped as to direct any pressure produced in said explosion chambers against said movable blades, a series of gas chambers adjacent to said explosion chambers, a valve between each explosion and gas chamber, means for supplying an explosive mixture to said gas chambers, means for producing explosions in said explosion chambers, a series of exhaust passages in said casing, and a series of stationary blades for directing the gases from the movable blades through said exhaust passages.

4. A gas turbine comprising a' casing, a shaft turning in said casing, a rotor mounted on said shaft, a series of movable blades on the periphery of said rotor, a series of explosion chambers in said casing, stationary blades in said casing extending inwardly and so shaped as to direct any pressure produced ary blades for directing the gases from the movable blades through said exhaust passages.

In testimony whereof, I have hereunto set l5 my hand at Los Angeles, California, this 24th day of February, 1914.

CYRIL Gr. PELLEY.

In presence of- FoRD W. HARRIS, FRED A.. MANSFIELD.