US825164A - Elastic-fluid turbine. - Google Patents

Description

ELASTIC FLUID TURBINE. APPLICATION PILED 001229, 1904.

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Witwzoow /l F P-" No. 825,164. PATENTED JULY 3, 1906.

E. TAYLOR. ELASTIC FLUID'TURBINE.

APPLIGATION FILED 00m 1904.

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E in 721 702" No. 825,164. PATENTED JULY 3, 1906. B. F. TAYLOR. ELASTIC FLUID TURBINE.

APPLICATION FILED 00129. 1904.

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uvzntoz Edwr'nf'jybr M, M $25 No. 825,164. PATENTED JULY 3, 1906. B. P. TAYLOR.

ELASTIC FLUID TURBINE.

APPLICATION FILED 00T.29.1904.

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lnuenfoz Edw/n 1? 7215/0)" q/vifneoaea FILE-- '7 2 No. 825,164. PATENTED JULY 3, 1906. B. F. TAYLOR. ELASTIC FLUID TURBINE.

APPLICATION FILED OCT.29. 1904.

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Jnvmfloz Edwin 721 /1 EDWIN F TAYLOR, OF /VYNOOTE, PENNSYLVANIA.

ELASTIC-FLUID TURBINE.

Specifi'cationof Letters Patent. Application filed October 29. 1904. Serial No. 230.536.

Patented July 3, 1906.

l condition. From this state the fluid is again To all whmizit may concern;

Be it known that I, EDWIN F.' TAYLOR, a

citizen of the United States, residing at Wyna cote, in the county of Montgomery and State of Pennsylvania, have invented certain new and useful Improvements in Elastic-Fluid Turbines; and I do herebydeclare the folj lowing to be a full, clear, and exact description of the invention, such as will enableothers skilled in the art to which it apper tains to make and use thesame.

This invention, which relates to elasticfluid turbines, contemplates certain new and useful improvements designed more especially for employment in-connection with the constructions of turbines for which Letters Pat-' ent numbered 752,602, 752,603, and 752,604

were issued to me on or about the 16th day of 1904; It is to be understood, however, that the present improvements are equally, capable of utilization in connection with other existing turbine constructions and no limitation is intended by the refernce to my patents above noted. Neither do I I limit the application of the improvementsto any particular class ofturbine, although I hive illustrated and describe hereinafter a multiple-wheel engine of the impact-reaction type embodying the present novel and useful features of construction.

Referring to my patented constructions above noted, it is patent that the motive fluid therein is expanded through a series of nozzle-sections and creates impact and reactive forces on blades or buckets carried by moving'parts located alternately between the successive nozzle-sections, which nozzle sections are so proportioned that an adiabatic partial expansion of the fluid may be effected in each section of the complete nozzle. The kinetic force of the fluid due to such expansion is accelerated at the point of impact through a change in entropy of the fluid immediately following its release from the noz,

zle-section and yields up its heat on the moving part in proportion to the degree of expansion created in the nozzle-section. The fluid having thus performed work through the me dium of the power-transmitting shaft by giving up its heat through impact in proportion to the degree of its expansion, assumes-a temperature corresponding "to the remainin pressure maintained and is again in a norma adiabatically partially expanded through a succeeding nozzle-section, the degree of this expansion corresponding to that of the previous expansion, and substantially the same degree of heat, together with substantially the same amount of energy, is therefore applied in the second stage, and so on through* out the range, all of the nozzle-sections bein constructed and arranged to deliver an equa amount of energy on each moving part of the series and to effect a continuous adiabatic expansion of the motive fluid. The degree of expansion of the fluid efiected in the nozzle-sections is determined by the velocity of and the degree of heat from the fluid required for the impact on the moving part, the nozzle-sections being proportioned to obtain the desired result. For example, in a highspeed turbine a lesser number of nozzle-sections are required, but said sections are necesf sarily proportioned to create an adiabatic partial expansion of the fluid to a lower presmanded in a slower-velocity turbine. It will of course be understood that a speed corresponding to the highest theoretical efliciency is to be-desired. Nevertheless turbines can be constructed along the stated lines to have Wide ranges of velocities with but slightlyimpaired efficiency.

One of the most difficult problems presented in turbine work is to not only maintain the efliciency throughout the range of load, but to construct a variable-speed turbine and maintain in its operation at various speeds sub-- stantially the same degree of efficiency.

- The present invention contemplates, among other valuable features hereinafter referred to and described, elements alternately active to create and to direct different degrees of energy against the moving part 'of the'tu'rbine. Said elements may each-consist of a nozzle or grou of nozzles capable of creating a degree of uid expansion differing from that created in the nozzle or group of nozzles constituting the other element, the differential elements commonly communicating with a fluidsupply and being alternately active to deliver varying kinetic forces against the impactsurfaces of the movable part, whererco by said part is caused to rotate at a greater or less speed, dependent upon the require The shaft is mounted at one end in a journal ments. It will be understood from the foregoing that the passage of the fluid is cut off from the one group of nozzlesfor example, the highexpansion group-while issuing from the other the lower expansion group and vice versa, and the means for accomplishing this alternate action constitutes another feature of the present improvements.

The manner of controlling the energy of the fluid by changing the degree of expansion through diflerential nozzle-sections is especially desirable and essential where different velocities are demanded and where substantially the same efficiency must be maintained. The outlined feature is an essential inmarine work, since the physical and climatic conditions demand a variable-speed turbine with the greatest degree of economy. It is to be understood that this feature, as

well as other features of my present invention, is applicable to turbines generally, although for the purpose of illustration I show and describe the improvements embodied in a turbine equipped especially for marine service and adapted for low and high speeds. v

The precise nature of the present improvements will now be disclosed, but only in their preferred forms of embodiment, the scope of the concluding claims permitting the various parts and combination of parts to be variouslymodified and departed from without exceedingthe intent of the invention.

- In connection with the detailed description reference is to be had to the accompanying drawings, in which Figure 1 is a side elevation of an elasticfluid turbine embodying my invention. Fig.

2 .is a vertical central longitudinal sectional view of the same intermediately broken away. Fig. 3 is a cross-sectional view on line 3 3 of Fig. 2. Fig. 4 is an enlarged sectional view on line 4 of Fig. 3. Fig. 5 is an enlarged view showing the construction and manner of assemblage of the insertible blades or buckets for a reversible moving part or wheel. Fig. 6 is a furtherenlarged similar view of the blades or buckets for a non-reversible moving part or wheel. Fig. 7 is a detail view of one of the blades or buckets for a reversible moving part or wheel.

Fig. 8 is an enlarged sectional view of one of the nozzle-sections and movable and stationary blades or buckets. Fig. 9 is an enlarged detail view of a wheel by which the control of the nozzle-sections is eflected. Fig. 10 is an enlarged sectional view of lower and higher speed nozzle-sections, valves therefor, and movable and stationary blades or buckets.

Referringto the drawings by'numerals, 1'

designates the turbine-casing, in which are a series of moving parts or wheels 2 2, fixed on a shaft 3, common to the entire series.

box 4, secured to and supported by a radially-ribbed casing-head 5, and is mounted toward its other end in a journal-box 6, supported from the base 7. The shaft-opening in the opposite casing-head 8 is suitably packed, as shown. The shaft terminates at its first-named end preferably within the j ournal-box 4 and is provided with a collar 9, forming an oil-guard to prevent the entrance of the lubricant into the interior of the casing. The journal-box 4 is covered by a cap 10, screwed between the threadedinner ends of the ribs and serving to exclude air from the casing-interior, as will presently be more fully explained.

The fluid-inlet 1 1 is shown in Fig. 1 and indicated by dotted lines in Fig. 2. This inpoint in the turbine where the fluid loses the major portion of its heat units and is more or less dependent upon the action of the condenser for its kinetic effect upon the moving parts in the condenser end. The heating? jacket serves, therefore, to'obtain the temperatures of the fluid at the several stages while the fluid is kinetically most active,

whereas when the fluid is deprived of the major portion of its kinetic energy and is dependent upon the condenser forfurther action, it is desirable from a standpoint of efficiency and economy to bring the fluid to as low a temperature as possible short of condensation and. within a minimum of time.

This result is accomplished by confining the heating means to the stages not influenced by the condenser which is connected with the fluid-outlet 16. The jacket is therefore not subjected to such a low degree of temperature as will cause condensation therein.

Neither are the stages influenced by the condenser subjected to the action of a heating medium. To obtain the best results from the employment of the heating-jacket, the

IIO

fluid between the inlet and chest is compelled to traverse a spiral path around the casing, spirally-disposed partitions 17 beinginterposed between the walls of the casing and jacket, as shown in Fig.2. i v

The moving parts, of which there may be any number, depending upon the.requirements, each consists of a disk 18, having balancing ball-weight races or grooves at its sides, and said disks are spaced apart by hubbed wheels19, having rims 20 and keyed or otherwise fixed to the shaft to rotate with the disks." Toward the periphery of each disk are two oppositelyefacing concentric series of blades or buckets alternately active to effect separate the rotation of the disk in opposite directions. The blades or buckets may be formed in the disk; but I prefer to construct them separately and interchangeable and fasten them on the disk-rim, as shown more clearly in Fig. 5. Each of the blades or buckets is provided with an inner impact-surface 21 and an outer impact-surface 22, facing a direction o posite to that of the surface 21 and d therefrom by a segmental portion 23. The blade or bucket terminates at its outer end in a segmental portion 24 and is provided near its inner end with a segmental portion 25, which rests against the periphery of the disk. The outer segmental portion 24 is provided at its opposite edges, respectively, with agroove 26 and a tongue 27, and the intermediate segmental portion 23 is similarly equipped at its edges with a groove 28 and a tongue 29. In assembled condition the blades or buckets are by the provision of the tongues and grooves radially interlocked, thereby effectually resisting the strain due to centrifugal action in rotation. The blades or buckets are fastened to the disk-rim by shouldered arms or shanks 3'0, drive-fitted into correspondinglyformed slots 31 in the disk. The shoulders 32 32 are located at'each side of and short of theinner end of an arm 30, with the result that when under strain displacement by the shoulders of the metal around the base of a slot is avoided and the shoulders alone are subjected to strain, which tends to shear them, but which is effectually resisted. To prevent fracture of the dis s between the slots therein, the arms and the slots into which they are fitted are alternately of different lengths and the shouldered ends are therefore in staggered relation, as shown.

Fig. 6 illustrates on a larger scale blades or buckets 33, provided with single im actsurfaces and adapted therefore fortur ines of the non-reversible type. The eculiar construction of the blades or buc ets by which they are caused to interlock with each other and with the disk enables them to effectually resist the strain due to the centrifugal force created by the revolving art. Inasmuch as the blades or buckets an the disk are drive-fitted together, the structure is rendered practically homogeneous with no tendency to separation by-reason of the provision for locking the blades or buckets at a plurality of points. The blades or buckets being fashioned each separately may be separately tested for stren by insuring against fracture or and displacement in operation.

The disks 18 extend at their'rim portions beyond the rims of the spacing-wheels 19 and between the walls of stationary chambers 34.

g theredlstortion The first disk of the ran e extends between the left-hand wall 35 of tile first chamber34 and the wall 14 of the fluid-chest 13. In the fluid-chest wall 14 and in the right-hand wall 36 of each stationary chamber are an inner set of adiabatic expansion-nozzle sections 37 and an outer set of similar nozzle-sections 38, one set being employed to effect the rotation of the moving part in one direction and the other set serving to rotate said part in the re-- verse direction, as will presently more fully appear. In the wall 35 of each of the stationary chambers are inner and outer concentric series of reaction blades or buckets 39, and by reference to Fig. 8 it will be seen that the construction of the movable and stationary blades or buckets is peculiar,- being designed with reference to each other and to the nozzle-sections to obtain the maximum efficieney in action. The blades or buckets are of concave-convex form, and, referring to the movable impact-blades 21, it will be noted that the are which forms the concave i mpactsurface of one blade is drawn from'a center, which is also the center of the are forming the convex surface of thenext adjacent blade. The fluid-passage between any two blades is therefore of uniform cross-sectional area throughout, and in said passages no fluid expansions may take place, the expansions occurring in the nozzle-sections alone. The stationary reaction-blades 39 are formed similarly to the impact-blades, but face in a direction opposite to that of the latter. Obviously the blades 39 may be formed separatelyfrom and fastened to the chamber-wall. The cross-sectional area of the passage between two reaction-blades is preferably substantially equal to that. between the im-- pact-blades, with the purpose of avoiding fluid expansion and scattering and dissipation of the fluid. The convex surfaces are formed of arcs and tangents, the tangential angles of the impact and reaction blade surfaces coinciding in order to maintain an equal cross-sectional area throughout the passages between the impact and reaction blades. This angle of the tangential line of an impact-blade convex surface also coincides with the angle Of'the'shOrter wall of a nozzle-section 37, whereby a portion of the passage between the blades 21 forms a (3011-. tinuation of, and consequentlylengthens, said nozzle-section, the line of divergence of said section being thereby maintained. A further and very important advantage due to the stated manner of extending the nozzlesection is that the fluid impacts against the moving surfaces at the most desirable point namely, near the change in direction of the passage. By this arrangement also the energies exerted at the 'sidesof the moving disk are practically equal-and the rotating disk is practically balanced between the impact and reactive forces. I I v Theffluid'passes from the steam-chest l3 through the outeror inner sets of nozzle-sections, dependent upon the desired direction of rotation of themoving parts "and said nozzle-sections deliver adiabati'call-y partially-expanded fluid against the. impact blades or bucketsofthe first disk. The fluid then moves against the blades. or buckets in the wall ofthe stationary chamber, creating a reaction effect on the disk, after which it enters the chamber, wherein it is in a normal condition. The fluid asses from the chamber throughthe nozz e-sections in the wall thereof and impacts'against the blades or buckets of the second disk, thence enters between the reaction-blades, and so on through out the range of moving parts. Theparts are proportioned to allow of the larger number of the disks receivingthe major portion ofthe kinetic energy of the fluid, and these disks are inclosed, as hereinbefore stated, by the heating-jacket 12. The remaining disks are within the influence of the condenser. Consequently the condenser action .on the fluid supplants its otherwise exhausted the bottom of the chamber.

kinetic energy, and a'heatin -jacket at these disks is therefore undesirab e. Thecap l0 effectually "excludes air from the condenser end of the turbine, thereby'insuring maximum efficiency of the condenser.

The stationary chambers are each divided by a continuous ring partition ,40, mounted to be rotated on rollers 41, which travel on The number and positions of the rollers will depend upon the requirements. The partition provides an inner annular chamber. for the fluid enter-.

ing from the inner nozzle-sections and blades or buckets and an outer annular chamber for the fluid entering from the outer nozzlesections and blades or buckets, the chambers.

being separated and non-communicating'in every position of the partition. The partition carries outer flange-sections 42 and inner flange-sections 43, and these sections in turn carry valves respectively numbered 44 and 45. By reference more particularlyto Fig.

3 it will be seen that there areprovided four groups of outer nozzle-sections and three groups of inner nozzle-sections, the outer nozzle-sections being employed to-eifect the rotation of the moving parts in one direction and the inner nozzle-sections serving to rotate the parts in the reverse direction. The

valves are yieldingly supported from the flange-sections throu'ghthe medium of bolts 46 and interposedcoiled springs 47. Q (See Fig. 4.) 'In' the position of thevalve's shown in Fig. 3 the first group'of outer diametrically opposite .nozzles a a is uncoveredand by partially'rotating the 4Q the second group of nozzles 6b is unc'overed,' the'first roup remaining open. Furtherrotatio'n oflthe-ring moves the valves to uncover the third group a 0, and in this position all of. the groups are open. The nozzle-sectionsof the three groups are proportioned to obtain apredetermined velocity, which is gradually reached by the, successive uncovering of the groups. Obviously the number of 'grpups and the number of nozzlesections comprising a group may be varied according to requirements. To obtain a-relatively higher rotative speed of the turbine, there are provided nozzle-sec tions d d, which are uncovered by the further movement in the same direction of the ring and valves. In said further movement the uncovered groups of nozzle-sections a, b, and c are closed by the ends 48 of the ad jacent valves and the openings between the valves are brought into position to open the stood. In this manner the maximum verotating the ring and valves the velocity is gradually reduced and the. turbine is not gle of the tangential line of an impact-blade convex surface coincides with the angle of the shorter wall of a nozzle-section, whereby a portion of the passage between two blades forms a continuation of and lengthens said nozzle-section. The higher de ee of en-i ergy created in the higherspee nozzle-sections d is the result of an increase in diver- .gence of the nozzle-walls, which increases the fluid expansion therein and also the result oflengthening the entire nozzle and changing the angle of inclination to bring the angle of its shorter wall to coincide with the angle of the tangential lines forming part of theconvex surfaces of the impact-blades. In further explanation of the action of the higherspeed nozzles it will be assumed, for example, 'thatthe fluid has an initial pressure of one hundred and twenty pounds absolute and that the groups of nozzlesa, b', and cin the first stage expand the pressure to one hundred pounds, thereby creating a velocity of nine hundred feet per second, which is twice the peripheral velocity of the moving part or four hundred and fifty feet per second. It will be further assumed, for example, that the higher velocity desired for the moving part is five hundred and seventy-five feet per second, re-

higher-speed nozzle-sections, as will be under- I locity is gradually reached, and by reversely sulting from a fluid velocity of eleven hundred and fifty per second, and to obtain this result the higher-speed nozzles, which communicate with the chest supplying the other nozzles, areconstructed and arranged to expand the fluid from one hundred and twenty pounds to, say, eighty pounds. The increased expansion for the higher speed has the effect of reducing the numberof stages acted upon by the kinetic energy, or, in other words, the Zero-point of kinetic, energy is changed. The stages not acted upon kinetically are subjected to windage action of the fluid, due to the influence of the condenser, and no loss in efliciency results.

Assuming that the movements of the ring and valves to uncover. the low and high speed nozzle-sections are clockwise, to effect the reverse rotation of the turbine the ring and valves are moved anticlockwise from their normal or stop position and reversing nozzle-section groups e f g are successively uncovered by the valves 45, carried by the inner flange-sections 43, thereby directing the fluid to and through the inner nozzle-sections, blades, and chambers. This wide range of valve adjustment is accomplished by the simple act of moving the ring 40 and valves,

which movements are accomplished, preferably, by a'pinion 49 and a segmental rack 50 on one of the fiange-sections 42. The pinions, which in number correspond to the number of moving parts, are housed in recesses 51 in the casing and, preferably at one side, as illustrated in Fig. 3. The showing in Fig. 2 of the valve-adjusting means at the top is for the sake I of clearness. The pinions are commonly fixed on a shaft 52, which extends beyond the casing-head and carries awheel 53, by which it is turned A pointer 54, movable with the wheel, and afixed dial 55, suitably marked, determine the direction and extent of movement of the valves.

By reference to Fig. 2 it will be noted that a material clearance is provided between the surfaces of a disk and the walls of adjoining stationary chambers. Owing to the uniform pressure of the body of fluid between the outlet of one nozzle-section and the inlet of the adjacentnozzle-section, there is no tenden'cy to leakage at the disks, and sufficient clearances may be provided to allow of a con siderable end thrust of the shaft and yet,

produce no friction between the surfaces. Between the inner wall 56 of a stationary chamber and the rim 20 of a wheel 19 there is, however, a tendency to leakage, which is avoided by providing in the wall-surface or rim-surface, or in both, recesses 57, forming a fluid-packed joint and creatin obstructions to the direct passage of flui between the wheel-rim and wall of the chamber.

I claim as my invention- 1. In an elastic-fluid. turbine, a moving part having surfaces, and a plurality of fluidnozzles alternately active to create and to direct with equal efficiency fluid at different velocities against said surfaces.

- 2. In an elastic-fluid variable-speed tur- 3.'I'n'an elastic-fluid turbine, a moving,

part having impact-surfaces, anda plurality of fluid-nozzles alternately active to create and to direct fluid at different velocities against said surfaces to move said part at different speeds which are each approximately one-half that of the velocity of the fluid.

4. In an elastic-fluid turbine, a heatingjacket communicating with the fluid-chest and surrounding the portion of the casing in which the fluid retains the major portion of its kinetic energy, and means for retarding the passage of fluid through said jacket.

5. In an elastic-fluid turbine, a heatingjacket through which the fluid passes to the chest, said jacket surrounding the portion of the casing in which the fluid retains the major portion of its kinetic energy, and means in said jacket forretarding thepassage of, the fluid therethrough.

6. In an elastic-fluid turbine, a heatingjacket surrounding the casing, and means for retarding, the passage of. the fluid therethrough. a I v 7 In an elastic-fluid turbine, a heatingjacket in communication with the fluid inlet and chest, and means in the jacket providing a spiral path for the fluid;

8. In an elastic-fluid turbine, a moving part consisting of a disk and a phn'alif'y ol' radially-interlocking impact blades or buckets removably fastened to said disk.

9. In an elastic-fluid turbine, a moving part consisting of a disk and a plurality of separately-formled interchangeable impact blades or buckets having means effecting their radial locking with each other and with the disk. e

10. In an elastic-fluid turbine, a moving part consisting of a slotted disk and a plurality of separately-formed impact blades or buckets having interlocking means and arms drive-fitted in said slots.

11. In an elastic-fluid turbine, a moving part consisting of a disk formed with radially-- disposed slots, and a plurality of radially-interlocking impact blades or buckets having shouldered arms drive-fitted in said slots.

12. In an elastic-fluid turbine, the combination of a rotatable disk having a plurality of radiallydisposed slots each having opposite lateral recesses located short of the slotbase, and a plurality of separately-formed impact blades or buckets each having a securing-arm formed with opposite shoulders located short of the end thereof, said arms fitting said slots.

13. In an elastic-fluid turbine, a rotatable disk having a plurality of radially-disposed slots the walls of whichgare intermediately and radially recessed, and a plurality of impact blades or buckets having securing-arms conforming to and fitting said recessed slots.

14. In an elastic-fluid turbine, a rotatable disk having radially-disposed slots, and a plurality of separately-formed impact blades or buckets having tongues and grooves whereby they are interlocked with each other and having shouldered arms interlocking with said slots.

15. In an elastic-fluid turbine, a rotatable disk havin radially-disposed slots, and a plurality 0% radial separately-formed interlocking impact blades or buckets having shouldered arms engaging said'slots said blades or buckets beingdrive-fitted to. each other and to the disk.

16. In an elastic-fluid turbine,a section of an adiabatic nozzle, a stationary fluid chamber having in one Wall reaction-surfaces and in the other Wall a second nozzle-secti on and arranged to maintain a uniform pressure between the outlet from the first-named nozzle-seotion and the inlet to the second nozale-section, and a movin part carrying impact-surfaces and rotatab e between the firstnamed nozzle and adjacent chamber-Wall.

17. In an elastic-fluid reversible turbine, a

stationary chamber having in one wall inner and outer series of passages and in the other I wallo' iner and outer series ofnozzles, and a rotatable ring filling the. chamber horizontally and dividingit into inner and outer fluid-passages' 18. In an elastic-fluid reversible turbine, a

inner and outer sets of impact-surfaoes and in the opposite wall inner and outer sets of nozzles, a rotatable partition dividing the chamber and carrying flange-sections, and nozzle-controlling valves carried by said flange-sections.

21. In an elastic-fluid reversible turbine, a stationary fluid-chamber having in one Wall inner and outer sets ofimpact-surfaces and in the opposite yvall inner and outer sets of nozzles, a rotatable partition dividing the chamber and carrying flange-sections, and nozzle-controlling valves yieldingl y carried by said flange sections. I

22. In -an elastic-fiuid reversible turbine, a

" stationary fluid-chamber having in one wall inner and outer-sets of impact-surfaces and in the opposite wall inner and outer sets of I nozzles, a rotatable partition dividing the chamber and carrying flange-sections, and

nozzle-controlling segmental valves carried' by said flange-sections.

23. In an elastic-fluid reversible turbine, a stationary fluid-chamber, and a roller-supported rotatable partition dividing the chamber horizontally.

, 24. In an elastic-fluid turbine, a fluidchamber having fluid-nozzles adapted to create difierent degrees of" energy, a ring in the chamber supported to be rotatable, segmental valves on the ring for successively controlling the valves, and meansfor rotating the ring and valves.

25. In an elastic-fluid turbine, a fluidchamber having fluid-nozzles adapted to create different degrees of energy, a ring supported to be rotatable and carrying segmental flange-sections, segmental valves carried by the flange-sections and arranged in the movement of the ring to successively control said nozzles.

26. In an elastic-fluid turbine, a stationary part, nozzles in said part, a ring supported to be rotatable, segmental valves on said ring and rack and pinion means for movin the ring and valves to successively contro said nozzles.

27. In an elastic-fluid turbine, a stationary part, nozzles in said part, a ring supported to be rotatable, segmental valves on said ring, rackand-pinion means for moving the ring andfvalvesto successively control said nozzles, a shaft for the pinion, awheel on the shaft, and a pointer and dial for determining the movements of the valves.

28. In an elastic-fluid reversible turbine, a stationary part, a concentric set of nozzles adapted to create different degrees of energy, a second concentric set of nozzles adapted to create different degrees of energy and to ro tate a movable part in a direction opposite to that of the first-named set, a ring rotatable between the sets, inner and outer valves carried by the ring, rack-and-pinion means for moving the ring and valves in either direction to successively control one or the other set of nozzles. I

29. In an elastic-fluid turbine, a chamber through which the fluid passes, disks carrying impact-surfaces and rotatable at the sides of the chamber, a spacing-wheel separating the disk and extending at its rim to the inner wall of the chamber, and fluid-recesses forming a fluid-packed j oint'between said wall and rim. v

, 30. In an elastic-fluid'turbine, a plurality I of moving parts, spacing elements for said parts, fluid-passages between said parts and means for preventing fluid leakage between the elements and passa e-Walls.

31. In an elastie-flui turbine, a plurality of moving disks, spacing-Wheels said disks, annular fluid-passages between the disks and beyond the spacing-Wheels, and means providing fluid-pecking between the Wheel-rims and passage-Walls.

32. In an elastic-fluid turbine, a. plurality of fluid-*ohembers through Which the fluid passeslaterally; a plurality of disks each moving With clearance between the sidewalls IO of two chambers, spacing-wheels separating I separating said disks and means providing fluid-packing between the wh el-rims and inner chamberwalls. In testimony whereof I eflix my signature in presence of two witnesses.

EDWIN F. TAYLOR.

Witnesses:

EDW. W. ANSTICE, LENA B. GOODFRIEND.

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