US2411798A

US2411798A - Gas turbine

Info

Publication number: US2411798A
Application number: US543574A
Authority: US
Inventors: Arthur H Matthews
Original assignee: Individual
Current assignee: Individual
Priority date: 1944-07-05
Filing date: 1944-07-05
Publication date: 1946-11-26
Anticipated expiration: 1963-11-26

Description

; Patented Nov. 26, 1946 s [PATENT OFFICE GAS TURBINE.

. Arthur H. Matthews, Lake Be'auport, Quebec,

Canad Application July 5, 1944, Serial No, 542,574

2 Claims; (01.60-41) expensive metals and in which provision is made for adequate cooling with minimum loss of power and efliciency. a

The commercial develope ment oi cheap and efllcient gas-turbines, especially in the smaller sizes required for general use, has been retarded by reason of the fact that the best gas-turbines heretofore proposed must be constructed of reltively rare and expensive heat resistant metals or alloys in order to withstand, for any considerable period, the destructive action of the high operating temperatures characteristic of such turbines. Gas-turbines constructed of ordinary metals and equipped with heat-dissipating water jackets in accordance with previous'proposals do not have the operating speed, efiiciency, low-cost characteristics and other essential requisites necessary to justify wide-scale commercial production thereof, especially in the smaller sizes suitable for general use in variousfields in which other types of relatively small power plants are now being used.

An important feature of the gas-turbine pro vided in accordance with my invention is '"that the rotor is of simple design and is free of vanes, buckets, or other resistance-increasing projections which, as employedin prior types of gas turbines, tend to decrease both the operating speed and the power output.

Another feature of the invention consistsin the provision of a generally improved gas-turbine in which the use of ordinary metals is made feasible by the use of water jets which serve both as a cooling medium and as a motive fluid.

A still further feature of the invention consists in the provision of a jet-propelled or reactiontype gas-turbine in which the rotor comprises a simple disk-shaped element provided with a peripheral channel into which jets of motive fluid are directed from nozzles or jets carried by a stator casing in which the rotor operates. at least one side wall of said channel being provided with discharge openings through which the motive fluid-is supplied to said channel in the form of jets which impinge against stationary buckets or vanes carried by the stator casing.

Other characteristic features and advantages of my invention will bemade apparent by the following detailed description of the accompanying drawing, in which- Fig. 1 is a vertical sectional view taken substantially along the line i-| of Fig. 2: and

upper half of stator-casing t to thereby effect Fig. 2 is a sectional view taken substantially along the line 2-2 of Fig. 1.

In this drawing the rotor and the stator-casing elements of my improved gas-turbine are respectively indicated at 5 and 8.

The rotor 5 is shown as a simple disk fixed to a shaft 1 which rotates in bearings 8 carried by opposite side walls of the stator-casing't. The periphery of the rotor is recessed to provide an annular channel 8. into which jets of fluid are directed from nozzles or jet passages it, ii and I2 formed in a removable section ta of the stator casing 6. At least one side wall of the channel 9 is provided with discharge ports M through which jets of the motive fluid suppliedto said channel are discharged against suitable stationary vanes or buckets i5 arranged around the jet-reaction operation of the rotor. The motive fluid is discharged from stator-casing 6 through the exhaust outlet i1,

Part of the motive fiuide supplied to the channel d of rotor 5 comprises hot products .of combustion resulting from ignition of a combustible fuel mixture with a combustion chamber it provided in the removable cylinder section ta. The

fuel mixture is supplied to chamber 89 through 9. Tesla" valve 2!) and is ignited by a spark plug 2! or other suitable igniter. The resulting products of combustion escape from chamber i9 through jet passage it and are directedinto the rotor channel 9.

Another part of the motive fluid supplied to the rotor consists of steam formed by vaporization of Jets of water which are directed-into the rotor channel 9 by the Jet passages ii and it. The

, cooling action of these jets of water is sufflcient to prevent heat-destruction of ordinary-metal used in the construction of the turbine.- The water is preferably supplied to the jet passages ii and 02 through Tesla" type valves indicated at 22 and 23.

The peripheral wall of the stator casing t is provided with a series of expansion chambers 25 into which the steam resulting from vaporization of the water jets directed against the rotor is I expanded to'increase the momentum imparted to the rotor. I

The hot products of combustion directed into the rotor channel 9 by nozzle it constitute the main motive fluid which drives and heats the rotor. The water injected through the jet passages I l and I2 serves primarily as a cooling medium but, when converted into steam as described herein, also serves as a motive fluid and enables 3 the turbine to be operated efflciently with a smaller amount of combustible fuel than would otherwise be required.

The combustion chamber I9 is provided with a removable cover or head 26 formed with a water' jacket 21 which is connected, by pipe 28, to waterjet valve 22. Cooling water is supplied to jacket 21 by a suitable supply pipe (not, shown) and passes from thence through pipe 28 and valve 22 to water-Jet passage II. The valve 23 of water-jet passage l2 may be similarly connected I claim:

1. A gas-turbine comprising a rotor provided with a peripheral channel having discharge ports in one side wall thereof, a stationary casing enclosing said rotor and provided with jet-passages through which expansible motive fluid is directed into said channel and stationary vanes or buckets in said casing located opposite the ported side of said channel and positioned to receive the impact of jets of motive fluid discharged from said channel through said ports.

, 2. A gas-turbine as set forth in claim 1, in which said rotor comprises a simple, substantially diskshaped member having its periphery recessed to provide said channel.

ARTHUR H. MATTHEWS.