US911492A - Turbine. - Google Patents

Description

R. H. GOLDSBOROUGH.

TURBINE.

T10]! mum mm. 4

Patented Feb. 2, 1909.

5 SHEETS-SHEET Z.

R. H. GOLDSBOROUGH,

TURBINE.

AAAAAAAAAA N FILED DEU 4.1908.

n 91 1,492. I I Patented Feh. 2, 1909.

R. H. GOLDSBOROUGH.

TURBINE.

APPLIOATIOH FILED 020.4, 1908. 91 1,492. Patented Feb. 2, 1909.

5 BBEBTS-BHEBT 4.

R. H. GOLDSBOROUGH.

TURBINE.

APPLIUATIUH FILED DBO. 4,1908 91 1,492. Patented Feb. 2, 1909.

5 SBEBTSSHEET 5.

RICHARD H. GOLDSBOROUGH, OF WASHINGTON, DISTRICT OF COLUMBIA.

TURBINE Specification of Letters Patent.

Patented Feb. 2, 1909.

Application filed December 4, 1908. Serial No. 466,011.

To ,all whom it may concern:

Be it known that I, RICHARD H. GOLDS- BOROUGH, a citizen of the United States, residing at Washington, in the District of Columbia, have invented certain new and useful Improvements in Turbines, of which the following is a specification.

My invention relates to turbines, and it consists in the constructions, combinations and arrangements herein described and claimed.

An object of my invention is to provide a compact and inexpensive turbine construction, which will have a high efficiency under all operative conditions.

A further ,obj ect of my invention is to pro.- vide .an improved repeateddmpact turbine, in which the steam between the several impacts will flow upon and be directed by the steam directed between the next preceding impacts.

A further object of my invention is to pro- .vide an improved turbine, in which the actuating steam will be directed to and through the rotor vanes in a compact body of greater cross-section than has been possible in previous constructions; thereby practically eliminating the wasteful leakage losses, andpermitting the employment of advantag ously large rotor clearance.

A further object of my invention is to provide an improved turbine, having radialflow rotor vanes of greater axial width than is practical in previous constructions, with a resultant minimization of the losses due to fluid and surface friction.

In the accompanying drawings, forming a part of this ap licationand in which similar reference sym ols indicate corresponding parts in the several views: Figure 1 is a central, vertical section, illustrating one embodiment of my invention; Fig. 2 is a detail perspective view of the rotor, with the securing and clamping rings partly broken away; Fig. 3 is a face view of one of the rotor vanes; Fig. 4 is an enlarged view of the rotor rim and cooperating stationary section shown at the lower portion of Fig. 1; Fig. 5

is a section on the line 55 of Fig. 4; Fig. 6

is an inner plan view of one of the stationary Sections Fig. 7 is a detail aXialsection, illustrating a modified form of stationary sec-, tion; Fig. 8 is an inner plan view of the section shown in Fig. 7; Fig. 9 is a fragmentary inner plan view, illustrating a slight modification of stationary section shown in Figs. 7 and 8, and Fig. 10 is a section on the line 1010 of Fig. 7.

Referring to the drawings, 1 indicates a turbine rotor, secured on a shaft 2 extending through suitable bearings 3 in the heads 4 of a casing 5. The rotor is provided with a a peripheral channel fi having rooves 7 in its Walls for positioning at an e cient angle an annular series of vane blades 8. The blades 8 are preferably formed of plates slidably fitting the grooves 7, and provided with shoulders 9 and 10 for engagement by securing rings 11 and 12,; said rings beingsecured to the rotor, as by screws 13, in position to overlap the grooves 7 and rmlyfengagethe peripheraledges of the bride shoulders 9 and 1 0.

A clamping ring 14 is shrunk, or otherwise suitably secured, about the medial portion of the periphery of the annular series of vane blades; a recess 15 being preferably formed in the peripheral edge of each vane for firmly seating said clamping ring. The ring 14 is shaped to constitute a continuous vane core, for providin the several vanes with U- sha ed passages iia'ving admission legs 16 an exhaust legs 17.

As shown especially in Fig. 4, the securing rings 11 and 12 constitute the eriphery of the assembled rotor, and the a ission and exhaustl s of the vanes terminate within such perip iery; the admission legs 16 being preferably beveled on both faces to rovide a knife edge 18, and the exhaust egs 17 beveled on their front faces to a knife edge 19. This improved vane construction with the securing rings 11 and 1-2 and clamping rin 14 minimizes the weight of the vanes an the action of centrifugal force thereon during operation. The securing rings positively lock the vane blades to the rotor, and the clampin rin engages the eripheral edges of sai blades in the radial plane of their center of gravity to rigidly clamp the blades from bending or distortion under the action of centrifugal force.

This invention provides radial-flow vanes of exceedingly greater axial width than is possible in revlous constructions; thereby permitting t e actuating steam to be direct-' ed through the vane passages in a volume of sufficiently large cross-section to minimize the losses of fluld and surface friction, and to ractically eliminate the wasteful leakage osses.

Any desired number of stationary sections 20 are secured alout the rotor for supplying steam to the vanes. As an example, with a rotor thirty inches in diameter nrovided with my improved vane constiuction. each section 20 can be conveniently g1 en a capacity of one hundred horse power.

The steam is conducted to the several sections 20 Ly independent pipes 21, thereiy emailing any desired numler of said sections to lie conveniently cut out for operating the turiine at maximum elliciency at various loads within its ca acity. Each section 20 comprises an arc-s iaped memlter provided with an initial port 28 for directing the actu ating steam to its first im act on the rotor vanes, and a common cham er for repeatedly directing the steam to successive impacts in a consolidated hod y of. circumferentiallydisposed steam layers; said common chamber icing provided with a rear guiding surface 27 and a front guiding surface 26 inclined to the periphery of the rotor at a smaller angle than said rear surface 27. The front and rear guiding surfaces donfine the consolidated steam Lody flowing through the common chaml er, and guide the successive steam layers thereof at progressively decreased angles to the rotor. A core 22 confines the steam in the common chaml. er, to a U-shaped passage of uniform transverse section; said passage comprising an admission port 23 for directing steam to the rotor vanes, an exhaust port 24 for receiving the exhaust from said vanes, and a deflecting passage 25 connecting said admission and exhaust orts.

In the operation of my invention, t 1e actuating steam is directed i the initial port 28 to the vanes, from whic it is discharged into the ad'acent rear ortion of the exhaust port 24. he steam t en flows throu h the deflecting passage 25, and is directed y the admission ort23 to the vanes; during such travel of t e steam between its successive impacts, it impinges upon, and is guided at an eflicient angle by, the rear guiding partition 27. The steam thus directed to its second impact with the vanes, is dlS( harged therefrom into the adjacent portion of the common exhaust ort 24 in juxtaposition with the steam discharged thereinto from the first impact; the steam discharge from the first impact constituting a fluid cushion for directing the discharge from the second impact. The dischar esfrom the first and second impacts then ow in a consolidated lzody throu h the deflecting passage 25, and are directe l y the common admlssion port 23 to the vanes in second and third impacts,

charge from the first impact is guided at an efficient angle by the partition 27 and the initial steam supply flowing past the inner edge of said partition, and the discharge from the second impact is guided at an elficient angle by the more rapidly flowing first discharge upon which it impinges. The steam is discharged from the second and third im acts into the common exhaust port 24, simu taneously with the discharge thereinto from the first impact; the several steam discharges flowing throu h the common chaml er in a consolidate body, in which each discharge im acts upon and is efiiciently guided by tie more rapidly flowing discharge from the )receding impact.

From the above escri tion, it will be seen that a single common c iamler. can he efficiently employed for any desired numl" er of repeated impacts of the actuating steam; the exhaust from the final impact discharging past the front wall 26 of the stationary section into the turline casing. Suitalle means, such as a conduit 29, is provided. for leading the final exhaust from the casing to any desired point.

My invention, thus, provides a construction in which a volume of steam is progressively directed along a helical ath to repeated impacts with the vanes: t 1e several steam layers constituting the spirals of such helical fiow impinging upon the preceding layers, and being efficiently guided thereby. 'lTjhis provides a highly advantageous construction, in which the surface friction incident to the employment of guiding blades or a multi )licity of nozzles is eliminated, and in' which the losses occa sioned by dispersion and fluid friction are minimized.

Fig s. 7 8 and 1.0 illustrate a modification in which the front end of the common tax-- haust port 30 of the stationary section 31 is open in free communication with the tur bine casing which receives the final exhaust. In this modification, I preferably employ a plate 32 for closing the front end of the common admission port 33, and extend said plate across the upper, or outer, portion of the common exhaust port 30. As shown in Fig. 10, the late 32 is sharply inclined. for rearwardly eflecting the relatively slowly flowing discharge impinging thereon from 3 the next to the final Impact; thereby causj ing such discharge to strongly impinge upon j the discharge from the preceding impact, and insuring an efficient consolidation of} the several steam layers in the common {125 chamber. An important advantage of this modification is that when the velocity of. the actuating steam has been so decreased 1 by repeated impacts that its speed is too low for efficient employment in a further impact, the relatively slowly moving discharge from the vanes will escape through the 0 en end of the common exhaust port 30; tins automatically preventing the loss of owel' caused by passing steam at an ine ciently low velocity through the rotor vanes.

Fig. 9 illustrates a slight modification, in which the front end of the admission port 34 of the stationary section is closed by an inclined late 35 similar to that previously described: and the front end of the exhaust port 36 of said section is formed radially and in free communication with the interior of the turbine casing.

I have illustrated and described preferred and satisfactory constructions, but changes could be made within'the spirit and scope of my invention.

Having thus described my invention, what I claim as new and desire to secure by Letters-Patent is:

1. In a turbine, the combination of a series of rotor buckets, and a common, curvilinear, inclosed assage or chamber rovided with front and rear guide walls and ing guide bar or core constitutingan inner wall of said chamber and dividing the latter into admission and exhaust ports, for receiving and reversing a plurality of steam currents, and for differentially directing such currents along paths of uniform length in a consolidated mass simultaneously into a plurality of said buckets, substantially as described;

2. In a turbine, the combination of a series of rotor buckets, and a common, curvilinear, inclosed passage or chamber provided with a Workin guide bar or core constituting an inner Wal of said chamber and dividing the latter into admission and exhaust ports, for receiving and reversing a plurality of steam currents,. and for differentially directing such currents along paths of uniform length in a consolidated mass simultaneously into a plurality of said buckets, said chamber being closed at both ends of its admission or nozzle port, and partially open at the farther and i only of its exhaust or receiving port for automatically by-passing or preventing the reentry of any part of en ch steam currents after the latter have been degraded by loss of velocity into a radial course, substantially as described.

3. Ina turbine. the combination of an annular series of vanes, and a common chamber for succcssivel y directing a volume of steam along paths of uniform length to progressively advanced portions of said vane series, substantially as described.

4. In a turbine, the combination of an annular series of vanes, and -a common with a Work chamber for directing .a circumferentiallydisposed series of abutting steam layers along paths of substantially e ual length to said vanes, substantially as ascribed.

5. In a turbine, the combination of an annular series of vanes, and a common chamber having an outer wall parallel to the periphery of said annular vane series for directing a volume of steam along a helical path successively to progressively advanced portions of said vane series, substantiallvcs described.

6. In a turbine, the combination of an annular series of vanes, and a common chamber for directing a volume of steam along paths of' substantially equal length to successive im acts on said vane series, substantially as (lbscribed.

7. In a turbine, the combination of an annular series of vanes, and a common chamber for directing a circumferentiallydisposed series of steam layers in a consolidated body to said vanes, said chamber being provided with a rear guiding surface inclined to the periphery of said annular vane series and with a front guiding surface inclined to such periphery at a less angle than said rear surface, substantially as described.

8. In a turbine, the "combination of an annular series of vanes, and acommon chamber for directin a circumferentially-disposed series of conso idated steam layers to said vanes, said chamber being provided with front and rear guiding surfaces extending at different angles to the peripher of said annular vane series, substantia y as described.

9. In a turbine, the combination of an annular series of vanes, and a common chamber for successively directing a circumferentially-disposed series of consolidated steam layers to progressively advanced portions of said vane series, said chamber being provided with a deflecting surface for rearwardly deflecting the several steam layers against the preceding la ers, and with front and rear guiding su aces for directing the consolidated steam layers at an efficient an le to said vanes, substantially as describe 10. In a turbine, the combination of an annular series of vanes, and a common chamber for directing a circumferentially-disposed series of steam layers in a consolidated body to said vanes, said chamber being provided with front and rear guiding surfaces for confining such cbnsolidated steam bod and guiding the several layers thereof at an efficient an le to said vanes, substantially as describecfi 11. In a turbine, the combination of an annular series of vanes, and a common chamber for directing a circumferentiallydisposed series of steam layers of different velocities in a consolidated body to said vanes, said chamber being provided with front and rear guiding surfaces for confining such consolidated steam body and guiding l the successive layersthereof at progressively decreased angles to said vanes, substantially as described.

12. In a turbine, the combination ol' an annular series of vanes, and a common chamber for directing a circumferentiallydis osed series of steam layers to said vanes, sai chamber being provided with a core extending circumferentially therein parallel to the periphery of said annular vane series for con ning the several steam layers, substantially as described.

13. In a turbine, the combination of an annular series of vanes and a common chamber for repeatedly directing a volume of steam alon paths of uniform length to said vanes, su stantially as described.

14. In a turbine, the combination of an annular series of vanes, and a common chamber constituting admission and exhaust ports for repeatedly directing a volume of steam along paths of uniform length to said vanes, such admission ort being closed at its front and rear ends guiding surfaces, substantially as described? 15. In a turbine, the combination of an annular series of vanes. and a common chamber for repeatedly directing a volume of steam along paths of uniform length to said vanes, said chamber com )rising an admission port closed at both en s by guiding surfaces, and an exhaust port having its front end in free communication with the final exhaust, substantially as described.

16. In a turbine, the combination of an annular series of vanes, and a common chamber for directing a volume of steam repeatedly along paths of uniform length to said vanes, said chamber comprising an admission port closed at its front and rear ends, and an exhaust port having its front and partially closed by a guiding surface, substantially as described.

17. In a turbine, the combination of a rotor provided with a peripheral channel,

an annular series of vane blades positioned in such channel and provided with medial l recesses in their peripheral edges, securing rings engaging the axial edges of said vanes,

and a clamping ring shrunk to a seat in such media] recesses of said vanes, substantially as described.

18. In a turbine, the combination of a rotor, a series of radial-flow vane blades detachable means for securing the axial edges of said blades to said rotor, and a clampin ring engaging the peripheral edges of said b ades at a point intermediate of said securing means, substantially as described.

19, In a turbine, the combination of a rotor provided W1th a peripheral channel, a series of vane blades extending across such channel, sccurin rings overlap )ing the axial edges of said b ades, and a c ampmg r1n extending medially about the periphera edges of said blades, substantially as described.

20. In a turbine the combination of a rotor provided with a peripheral channel having grooved Walls, vane blades extending Within such grooves, securing rings overlapping such grooves, and a clamping rin medially engaging the peripheral edges 0 said blades to constitute a continuous vane core, substantially as described.

2].. In a turbine, the combination of a rotor rovided with a peripheral channel, vane b ades extendin across such channel, and a series of space detachable rings engaging the peripheral ed es of said blades, substantially as describec.

In testimony whereof I allix my signature in presence of two Witnesses.

RICHARD H. GOLDSBOROUGH.

Witnesses:

G. Avnns, B. M. Orru'r'r.

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