US1291273A

US1291273A - Gas-turbine.

Info

Publication number: US1291273A
Application number: US22204418A
Authority: US
Inventors: Alva W Tyler
Original assignee: Individual
Current assignee: Individual
Priority date: 1918-03-12
Filing date: 1918-03-12
Publication date: 1919-01-14
Anticipated expiration: 1936-01-14

Description

A. w. TYLER.

GAS TURBINE.

APPLICATION FILED MAR. 12, 1918.v

mem@ Jan.14 ,m19.

2 SHEETS-SHEET 2.

To all 'whom t may concern.'

Be it known thatl, ALVA W. TYLER, citizen of the United States, residing at Los Angeles, in the county of Los Angeles, State 5 of California, have invented new and useful Improvements in Gas-Turbines, of which the following is a specification.

This invention relatesto internal combustion motors of theturbine type.4 Tt is one of the objects of this invention to provide a simple turbine structure in which there is but virtually one moving part which is the rotating part, in which there are no reciprocating parts and no valves, valve seats or cams, cam shafts or other similar valve operating mechanism; to provide a structure in which the energy of an expanding gas is delivered directly to the rotating parts without the intervention of intermediate members or mechanisms;vand to provide a motor having few parts and having'relatively high efficiency. And there are several other objects appearing in the following specification.

T provide means for causing the etlicient expansion, and the edicient use of the energy of expansion, of the `heated gases by providing anovel arrangement and spacing of the vanes or blades into which the expanding gases are initially discharged from the combustion chambers. I also provide means for causing the thorough scavenging of the combustion chambers prior to the introduction of a new charge. t Tn such a turbine as herein described, my preferred construction includes a combined reaction and impulse arrangement; the vanes or biades being so shaped and spaced as to provide such action. blades are also shaped and spaced to lprovide 'for uniform and steady dow and expanand continuous application of power to the rotating parts. T further provide, in. a specie form, a reversible turbine. These features, and others, will be understood from the following description of a erence being had to the illustration of said in which Figure 1 is a verticalcross section of a preferred form of turbine; 'Fig 2A is a longitudinal vertical section taken as indicatedby line 2-2 on Fig. 1; Fig. 3 is a reduced diagrammatic view taken as indicated by line 33 on Fig.v 2; Fig. d is sra-Tas PATENT MVA. W. TYLER, F IIilfll ANGELES, GALIFORNIA.

The vanes or.

sion of the gases, and consequently uniform preferred embodiment of my invention, refembodiment in theaccompanying drawings .solid or blank parts lorries.

GAS-TURBN'E.

Specification ofletters Patent.

Patenteddan. f4, 1919..

nppneanon inea Maren 1e, isis. semi no. 222,044.

an enlarged detailsection showing the preferred form of vanes and nozzle outlet for\ the combustion chambers; Fig. 5 is a partial section, taken -on line 5-Y-5 of- Fig. 6, showing a reversible form of turbine; Fig. 6 is a section taken on line 6-6'of Fig. 5; and Fig. is a detail section taken on line 7-7 of Fig. 6.

Tn the drawings T show a construction in which the innermost memberthe one containing the explosion chambers-forms a part of the motor; and in which the ex pansion vanes are arranged for outward radial transmission of the expanding gases. But T do not restrict myself to radial flow;

and it will be obseryed that, in general, these bers 14E arranged in the relative positionsillustrated. ,Flach of these chambers has an outlet nozzle 1 5, which extends across the face of rotating member 13. These nozzles point `in direction oblique to a tangent drawn to the circumferencel of member 13 at the nozzle outlet and the `angle of this Obliquity may be made such as to suit conditions and such as to cause the most efficient discharge of the expanding gases into the vanes of the immediately surrounding stationary member 16. The combustion chambers are also arranged so that the How of expanding gases from their rear ends to their discharge nozzles shall be direct and uninterrupted. This is an important feature in connection' with the scavenging of the chambers, as hereinafter described.`

The stationary member 16 immediately surrounding the rotating member 13 is made up of successive portions which ll may term l the charging and expanding portions. The

charging portions of this member are merely nozzles of the combustion chambers as they pass these parts. The expansion parts of this member are provided with vanes 18 into ,which the expanding gases are directed by the nozzles `;-and the exhaust ports of to the invention here de- 17, which close od' the through passages 20.

transversely to atmosphere, as shown at 2()n in Fig. 6. Central web 21 is, or may be, a part of the outer cylindrical casing 22 of the turbine; and is the means of anchoring the stationary vanes and of anchoring 'the

parts

17 and 19. Generally speaking, the stationary member 16 may be anchored to, or be integral with, the central web 21.

The central rotating member 13 rotates' in the direction indicated by the arrow;

' and means are provided, as hereinafter ex- 4'plained, for igniting the mixture in each combustion chamber in proper time to have the expanding gases expand outwardly through the vanes 18. that the vanes 18 are progressively spaced farther and farther from each other in the direction of rotation. This means that when the pressure in the combustion chambert-(is high, at the beginning of the expansion period, the space between the vanes is correspondingly small to pass a given quantity or mass of gases under high pressure; while, when the pressure is low, at the end of the expanding period, the space between the vanes is correspondingly wide to pass the same given quantity or mass of gases under low pressure. This has the effect of keeping` the velocity of the gases in each compartment between' vanes maximum during the expansion period until a pressure at or near atmospheric pressure has been reached; and since the discharge area of the low pressure vanes is relatively larger they embrace a correspondingly larger number of rotating Vanes, thus giving a uniform reaction for each compartment.

The gases which pass through the vanes 18 then pass progressively through surrounding sets of

vanes

25, 26 and 27, and

then inally exhaust at atmosphere through the open cylindrical casin 22. The vanes 25vrotate; vanes 26 are stationary and vanes 27 again rotate. 0f course it will be understood that I may have any number of alternately stationary and moving sets of vanes. The'number here shown is merely typical.

Vanes

25 and 27 are mounted upon side anges 30, which in turn are mounted upon, and rotate with, the rotating member 13. The stationary varies 18 and 26 are mounted uponthe central web 21. As hereinbefore stated, I have shown these sets of vanes arranged concentrically, one around the other, and arranged and designed :tor

radial passage of the expanding gases. Although this is not an essential element of j may be eiiciently air cooled by the rotation `proper times to carry on the sequence of Now it will be noted sages 40 passes a port 42. When a passage tions 17 of member 16, the nozzle outlet bemy invention, yet it has certain advantages. With the parts arranged as shown, they of flanges 30 and member 13 in the atmosphere. The frame 10 is open so as to allow free access of the atmosphere to the rotating parts; and to allow artificial cooling, if desired, by artificial air currents, etc.

I provide mechanism, now about to be described, for causing the charging, the firing and the scavenging of the combustion chambers in the proper sequence and at the operations herein described. Each of the combustion chambers has an intake passage 40 extending radially out to the combustion chamber from the interior oiE hollow shaft 12.. These intake passages communicate with the respective combustion chambers at their rear ends; that is, at their ends farthermost from the expansion outlet nozzles 15. Within the hollow shaft 12 I place a stationary sleeve 41; and this stationary sleeve is provided with ports 42 of the same number as the number of intake portions 17 in the member 16. In the turbine herein described, there are three of these portions, and therefore three ports 42; and each of the ten combustion chambers 14 goes through three complete cycles of operation during each revolution; making thirty explosions in this turbine for each revolution. anchored in a suitable anchor bearing 43, being adjustable in position so as to adjust the position of ports 42. The member shown at 44 is engageable by a wrench to adjust the position of the sleeve; or any other suitable means of adjustment may be used.

The previously prepared explosive mixture is fed tothe turbine under pressure through a pipe 45 having a connection at 46 with sleeve 41, allowing the sleeve to be rotatably adjusted. Within sleeve 41 I provide an interior throttle sleeve 47 with ports A 46 adapted t0 be more or less fully registered with the sleeve ports 42. This throttle sleeve 47 may be rotated through the medium of arm 49, for the purpose of controlling the charge delivery to the conibustion chambers.

Immediately before the inlet passages 4() registerI with .ports 42 they register with small ports 50. These ports 50 are connected by ducts 51 with a'compressed air inlet to which compressed air may be supplied through a pipe 53. When the turbine is in operation, the following cycleot operations takes place for each time that one of the pas- 40 comesinto register with a port 42 then the outlet nozzle 'of the corresponding chamber 14 1s just passing onto one of the intake por- The outer end of sleeve 41 is.

i 1` ber 14 is at the end 42 being incommensurate, occur simultaneously;

ing thus closed. Explosive mixture under ressure is forced into the combustion chamer l4'during the period of passage across the charging portion 17. Immediately the nozzle reaches the end of this portion, it then passes into communication with vanes 18 and at or before this time the compressed charge in the chamber isignited by means of spark plug 55. Thesubsequent burning and expansion of the gases causes their' How through the various vanes and causes the continued rotation of the rotating parts. The position of the spark plugs 55 close to the nozzle iiisures the rst ignition and expansion of the gaseous charge close tothe nozzle, thecombustion then proceeding back to the rear or inner en'd of the chamber. This precludes the possibility of any unburnt orfresh gases being forced out of the nozzle, and insures that the combustion shall take place in the combustion chamber and not in the vanes. By the time the nozzle has passed the vanes 18, the pressure in the chamber 14 has been reduced to or near atmospheric pressure. The major exhaust of the burnt gases takes place outwardly to atmosphere through the sets of vanes. The nozzle then passes into communication with the exhaust chamber 19 through which the remaining gases escape to atmospheric pressure (br below atmospheric pressure, due to the centrifugal throwing out of the gases from chamber 14), During the latter part of the exhaust period, the iny take passage 40 comes into register with one of the compressed air ports and com pressed air is allowed to How into the chamber 14 at its inner end, forcing out any remaining burnt gases. It will now be noted that the connection of passage 40 with chamfarthest from the discharge nozzle .and that, consequently, forcing in of compressed air at this point will completely scavenge the chamber of burnt gases I"and will leave the chamber filled with ya charge of clean, fresh air under approximately atmospheric pressure. The pressure necessary to introduce the'fresh air may, in some circumstances, be very little more, if any more, than atmospheric; as the centrifugal forces have a tendency to throw the burnt gases out of the chamber and thus create a partial vacuum therein; This final scavenging of the chamber and introduction of fresh air thereto takes place just before 'if L- the outlet nozzle passes again onto a charging portion 17, and l onto this charging portion the intake passage when the nozzle passes 40 then passes'into the register with the next port 42, causing the chamber to be again A charged. This complete i* is repeated, in this particular instancethree k times in each revolution. The ratio of the cycle of operations number of chambers to the number of ports no two explosions and -there being thirty justed and regulated;

The foregoing description applies gen erally to all the forms of structure shown in the various drawings. In Fig,'4 I show the details of av preferred form of blades or vanes, and lalso of the nozzle outlet of the combustionl chamber. In this 4structure I show the vanes 18 spaced in the manner. 85 hereinbefore described; andv I show them of such configuration, that, at the point 18a, each space between the vanes, there is a comparative constriction. That is, the spaces between the vanes at 18b narrow down to- 90 ward the point 18a and then expand at 18. This narrowing of the spaces gives more or less of a nozzle effect and prevents the eX* pending gases escaping too quickly from the chambers 14. The preferred form of nozzle outlet 15, from chamber 14, is also shown in this view, the nozzle having a constriction at 15a and then expanding somewhat toward its end-so as to allow a maximum velocity of the gases at the outlet. Each 10a one of the spaces 18b takes the expanding 4gases from the chamber 14, and these eX- of the expanding gases through and from I the vanes 18, so as to more evenly distribute the power application and make a more continuous application of power to the rotat ing element ofthe turblne.

In Figs. 5, 6 and 7 I illustrate a form 115v of turbine which is, in essentials, the same as the formshown in the other views, excepting that it is equipped-With a reversing mechanism.

In this form of'turbine I divide each of 120 the sets of

vanes

18, 25, 26 and 27 by central partitions 100 into separatedsets 18f 25', 27|f and l8r, 251", 26r and 27T. Those vanes denoted by the numerals with sufixed f are arranged to cause rotation in one direction; while those with suffixes r cause rotation in the opposite direction. For the purposes'of this reversing form, I arrange the combustion chambers 14 radially lin the member 13, and at the Outlet end of each eonilnistion chamber, vI malte a V-shaped opening 101 extending across the face of member 1?. In each of these openings I place a reversing block 102 adapted to be shifted eircuinferentially a short distance. The blocks and openings are of such relativel sizes that a nozzle outlet space 103 is left on one side or other of the block. the drawings the parts are'shown iii position to' cause rotation in the direction indicated. The nozzle outlet space 103 shown open in the drawings is restricted to the opposite sides of the member 13 b v a central flange 104 of the block which covers up the central part of this nozzle opening 1.03, restricting the escape of the expanding gases to the uncovered parts of the opening 103, in the positions shown distinctly in F ig. (l. The other side of each block has flanges 105 at each side. lhen the blocks are shifted circuinferentially to form the nozzle opening 103 on the other side of the blocks, then the gases escape centrally at that side of the block, being prevented from .escaping at the ends of the block b y the flanges 105. Yhen the gases escape through this central opening at the other side of the block, they escape in such a direction as to properly1 iinpinge upon the vanes 18; and the turbine is thus caused to rotate in the direction opposite that indicated by the arrow.

The blocks 102 are Secured to and between side rings 110. Studs 111 majv be mounted in these side rings and extend through the side members 30 of the revolving member 13 and are secured to a ring 112. This ring 112 may be rotatably adjustable upon the shaft 12 in any desired inanncr. .Suitable means Imay be employed for holding the blocks 102 in their positions when once set; or there may be sufficient friction present to hold them without any special arrangements to that effect.

I provide aturbine in which there is a direct application of the energy of expanding gasesto the rotating parts, and in which there are no operating parts intermediate. The valve mechanism is relativelyv simple; and the turbine includes essentially but one moving part and that the rotating part. There is an absence of internal friction surface and, therefore, no need for internal lubrication of hot rubbing parts. In fact, there is no friction in niy engine except that of the main bearings, and the friction of the small surfaces of the internal sleeve valve. This friction is small, and the valve surface is easily lubricated and, moreover, is cooled by the incoming charge of fresh gas. Excepting these valve surfaces and the bearings, there are no wearing parts.

And, in spite of this simplicity, there is h igh elliciency of gas expansion and of application of energy to the rotating element.

These are outstanding features of my invention and various forms of structure ma v be designed and built to include one or all of them. I therefore do not limit in vseli" to the specilie einlanliment herein shown, except as stated in the following claims.

lVhat I claim is:

1. In a` gas turbine, the combination of a pair of relatively rotatable elements; one of said elements having combustion chambers therein and the other of said elements carrying vaiies adapted to receive the expanding gases fronrthe combustion chambers, said vaiics being progressively spaced wider apart in the direction of the rotation of the first mentioned clement relative to the second mentioned element. Y

In a gas turbine, the combination of an inner rotating clement and an outer stationar \v element; said inner rotating element. having combustion chambers with outlets at its periphery, and said outer stationary element having successively around its periphery, parts provided with vanes to receive and react against the expanding gases from the combustion chamber outlets and parts havingexhaust openings leading to atmosphere; the number of said coinbustion chambers and the number of said parts in the outer element being iiicoinmeiisiirate.

3. In a gas turbine, the combination of two relatively rotatable elements, one of said elements having combustion chambers therein, and the other of said elements having arranged in succession 'therearound parts having vancs adapted to receive and react against expanding gases frointhe combiistioii chambers and parts having exhaust openings leading to atmosphere; the nuinber of said combustion chambers .in one element and the number of said parts in the other element being incommensurate.

1. In a gas turbine, the combination of tivo relatively rotatable elements, one of said chambers with outlets leading diagonally to the periphery of the element, a hollow shaftv carrying said element, there being an inletJ passage for each. combustion chamber leading from the inner end of the combustion chamber opposite the outlet to the Vinterior sleeve valve being 1 rotatably adjusta l the sleeve valve having ports adapted to be 1` registered with the sleeve valve ports, means for feeding combustible mixture into-the l l, of the hollow shaft, a. stationary ported -jj valve sleeve within the hollow shaft, means for feeding combustible mixture into the valve sleeve; a stationary element around the rotatable element, said stationary 'element having arranged successively around its periphery in the direction of rotation of the rotatable element parts which present a solid blank to close the combustion chamber s outlets whenl opposite them, parts having 5'; vanes adaptedto receive expanding gases j, from the combustion chambers, and parts j; having exhaust openings leading to atmos- -fIL phere, said vanes being successively spaced wider and .wider apart in the. direction of ij rotation of the rotatable element.

6. ln a gas turbine, the combination of -F an inner rotating element having therein g near its periphery a plurality of combustion -chambers with outlets leading diagonally to the periphery of the element, a hollow shaft carrying said element, `there being an lf' inlet passage for cach combustion chamber leading from the inner end of the combustion chamber opposite the outlet to the interior of the hollow shaft, a stationary ported valve sleeve within the hollow shaft, said sleeve valve being rotatably adjustable, a rotatably adjustable throttle sleeve'within the sleeve valve having ports adapted to be L registered with the sleeve valveports, means for feeding combustible mixture into the )fj throttle sleeve; a stationary element around the rotatable element, said stationary elef inent'having arranged successivelyV around its periphery, parts which present a solid blank to close the combustion chamber outlets when opposite them, parts having vanes adapted to receive expanding gases from the combustion chambers, and parts having exhaust openings leading to atmos here.

7 ln a gas turbine, the combination of an inner rotating element having therein near its periphery a pluralityA of combustion chambers with outlets leading diagonally to the periphery of the element, a hollow shaft carrying said element, there being an inlet passage for each combustion chamber leading from the inner end of the combustion chamber o posite the outlet to the interior of the hol ow shaft, a stationary ported valve sleeve within the hollow shaft, said' rotatably adjustable, a e throttle sleeve within throttle sleeve; a stationary element around the rotatable element, said stationary-element having arranged successively around it Q periphery parts which present a solid blank to close the combustion chamber outletsf n when opposite them, parts vhaving vanes adapted to receive a react.- against expandin ceses from the combustion chambers, al1

parts having exhaust openings leading to atmosphere, said vanes being successively 'spaced wider and wider apart in the direcpassage foreach combustion chamber leading from the inner end of the combustion chamber opposite the outlet to the interior of the hollow shaft, a stationary ported valve sleeve within the hollow shaft, means for feeding combustible mixture into the valve sleeve; a stationary element around the rota: table element, said stationary element having arranged successively around its periphery, in the direction of rotation of the rotating "element parts which present a solid blank to close the combustion chamber outlets when opposite them, parts having vanes adapted to receive expanding gases from thecombustion chamber, and parts having exhaust openings leading to atmosphere, the arrangement being such that the inlet passages come into registery with the sleeve valve ports when the corresponding combustion chamber outlets are closed by said blank portion of the stationary element; and means in conjunction with said valve sleeve to' introduce fresh air to the chambers through their inlet passages during the registry of thecombu'stion chamber outlets with the' exhaust openings in the 100 stationary element. v

9. In a gas turbine, the combination of an inner rotating element having therein near 4its periphery a plurality of combustion chambers with outlets leading diagonally to.

i theperiphery of the element, a hollow shaft carrying said element, there being an inlet assage ,for each combustion chamber leading from the inner end of the combustion chamber opposite the outlet to the interior of the hollow shaft, a stationary ported valve sleeve within the hollow shaft, ,means fOr feeding combustible mixture into the valve sleeve; a stationary element around the rotatable element, said stationary element hav- 116 ing arranged successively around its periph,-

ery in the direction of rotation of the rotating element parts which present a solid blank to close the combustion chamber outlets when opposite them, 4parts having vanes adapted 120'- to receive expanding gases from the combustion chambers, `and parts having exhaust 4openings' leading to atmosphere, said `vanes being successively spaced wider and wider.

apart in the direction of rotation of the ros 126;

tatable element.

10. In a gas turbine, the combination of an inner rotating element having therein near its periphery a pluralit of .combustion chambers with out ets les ,ing diagonally to 139 the periphery of the element, a hollow shaft carrying said element, there being an inlet passage for each combustion chamber leading from the inner end of the combustion chamber opposite the outlet to the interior of the hollow shaft, a stationary ported valve sleeve within the hollow shaft, means for feeding combustible lnixture into the valve sleeve, a stationary element around the rotatable element, said stationary element having arranged successively around its periphery in the direction of rotation of the rotating element parts which present a solid blank to Close the combustion chamber outlets when opposite them, parts having vanes adapted to receive expanding gases from the combustion chambers, and parts having exhaust openings leading to atmosphere, said vanes eing successively spaced wider and wider apart in the direction of rotation of the rotatable element; and alternate rotatable and stationaryelements with vanes surrounding said first mentioned stationary element to receive the expanding gases passing outwardly from the vanes in the first mentioned stationary element.

11. In a gas turbine, the combination of a pair of relatively rotatable elements; one of said elements having combustion chambers therein and the other of said elements carrying vanes adapted to receive and react vagainst the expanding gases from the combustion chambers, said vanes being progressively spaced wider apart in the direction of the `rotation of the first mentioned element relative to the second mentioned element, and the spaces between said vanes being constrieted in the direction of How of the expanding gases.

12. In a gas turbine, the combination of two relatively rotatable elements, one of said elements having combustion chambers therein, and the other of said elements having arranged in succession therearound parts having vanes adapted to receive and react against the expanding gases from the combustion chambers andl parts having exhaust openings leading to atmosphere, the said vanes in said second mentioned element belng spaced successively wider and wider apart in the direction of rotation of the first mentioned element relative to the second mentioned element, and the spaces between said vanes being constrieted in the direetion of flow of the expanding gases.

13. In a gas turbine, the combination of an inner rotating element having therein near its periphery a plurality of combustion chambers with outlets leading diagonally to the periphery of the element, a hollow shaft carrying said element, there being an inlet passage for each combustion chamber leading from the inner end of the combustion chamber approximately opposite the outlet to the interior of the hollow shaft, a stahaving vanes adapted to receive expanding gases from the combustion chambers, and parts having exhaust openings leading to atmosphere, said vanes being sum-essively spaced wider and wider apart in the direction of rotation of the rotatable element, and the spaces between said vanes being con- -stricted in the direction of flow of the expanding gases.

14. Ina gas turbine, the combination of an inner. rotating element having therein near its periphery a plurality of combustion chambers with outlets leading diagonally to the periphery of the element, a hollow shaft carrying said element, there being an inlet passage for each combustion chamber leading from the-inner end of the combustion chamber opposite the outlet to the interior of the hollow shaft, a ported sleeve valve within the hollow shaft, said sleeve valve being rotatably adjustable, a rotatably adjustable throttle sleeve within the sleeve valve having ports adapted to be registered with thc sleeve valve ports, means for feeding combustible mixture into the throttle sleeve; a stationary element around the rotatable element, said stationary element having arranged successively around its periphery parts which present a solid blank to close the combustion chamber outlets when opposite them, parts having vanes adapted to receiveand react against expanding gases from the combustion chambers, and parts having exhaust openings leading to atmosphere, said vanes being successively spaced wider and wider apart in the direction of rotation of the rotatable element, and the spaces between said vanes heilig constricted in the direction of iow of the expanding gases.

15. In a turbine of the character described, the combination of a pair of relatively rotatable elements, one of said elevanes ybeing progressively larger and larger in the direction of rotation of the first mentioned element, andthe spaces between said vanes being constricted in 4the direction of flow of the expanding fluid so as to hold' and retard the How of expanding fluidi between said vanes. 4 4

17. ln a gas turbine, the. combination of an inner rotating element having therein near its periphery a plurality of combustion chambers with outlets leading diagonally to the periphery of the element, a hollow shaft carrying said element, there, beingan inlet passage for each combustion chamber leading from the inner end of the combustion chamber approximately opposite the outlet to the interior of the hollow shaft, a stationary ported valve sleeve within the hollow shaft, meansk for feeding combustible mixture into the valve sleeve; a stationary element around the rotatable element, said stationary element having arranged successively around its periphery, parts which present a solid blank to close the combustion chamber outlets when opposite them,

parts having vanes adapted to receive expanding gases from the combustion chamers, and parts having exhaust openings leadin to atmosphere, said vanes being successive y spaced'wider Aand wider apart in the direction of rotation of the rotatable element, and the spaces between said vanes being constrieted in the direction of `How of the expanding gases.

18. -lln a gas turbine, the combination of a pair of `relativelyrotatable elements, one

of said elements having radially` arranged combustion chambers therein, and the other of said elements ,having vanes adapted to receive and react against the expanding gases from the combustion chambers, said vanes being divided into two parts, one'part formed for causing rotation in one direction and the other for causing rotation in the opposite direction, and means on the first mentioned element for 'directing the expand ing gases from the combustion chambers in either of two tangentially opposite directions into either of said parts o the vanes.

19. lln a as turbine, the combination of two relative y rotating elements, one of saidelements having therein a combustion cham.

ber with an outlet at the surface of the ele- A fr 20. lin a gas turhiue, the combination of two relatively rotating elements, one of said elements having therein a combustion chamber with an outlet at the surface of the element adjacent the other element; the other element having thereon, in arrangement to be successively traveled over by the combusf tion outlet, a pari which presents a blank wall to the combustion outlet, then a 'part provided with means for causing rotation by action of the expanding gases from the combustion out-let and leadmg to atmosphere; means to feed combustible mixture under pressure to the chamber during passage of the first mentioned part, means' to cause combustion in the combustion chamber during passage of the first portion of the second mentioned part, and means to feed in fresh air under pressure during passage of the remainder of the second mentioned part.

.21. In a gas turbine the combination of a pair of relatively rotatable elements, one of said elements having two sets of vanes arranged for causing rotation in opposite directlons; the other element having combustion chambers leadin to the periphery of the element, and mova le deflecting inembers mounted in the peripheral part of said element to deflect the expanding gases from the combustion chamber in either one 0r the v.other of the two opposite tangential directions.

In witness that I claim the foregoing I day of February, 1918.

ALVA W..TYLER.

Witness:

V. I. BERINGER.

have' hereunto subscribed my name this 26