US3091429A - Turbines - Google Patents

Description

0. THElME R May 28, 1963 TURBINES Filed June 8. 1960 0. THElMER May 28, 1963 TURBINES 7 Sheets-Sheet 3 Filed June 8, 1960 INVENTOR. @rm% May 28, 1963 Filed June 8, 1960 O. THEIMER TURBINES 7 Sheets'-Sheet 4 IN V EN TOR.

May 28, 1963 Filed June 8, 1960 O. THEIMER TURBINES 7 Sheets-Sheet 5 Elk 0. THEIMER May 28, 1963 TURBINES Filed June 8. 1960 7 Sheets-Sheet 6 o. THEIMER 3,091,429

TURBINES 7 Sheets-Sheet 7 May 28, 1963 Filed June a. 1960 I ENTOR. 49 m United States Patent Ofi Patented May 28, 1963 ice sperms TURBENES Oscar Theimer, 35 Fort Washington Ave, 43, New York, N.Y. Filed June 8, 1960, Ser. No. 34,766 3 Claims. (Cl. 253-39.15)

This invention refers to improvements relating to turbines, in particular to the tunbine rotor as disclosed in my US. Patent No. 2,542,549 issued October 3, 1950, and to further improvements disclosed in my application Serial No. 450,180 filed August 16, 1954, now abandoned, and especially to my improvements disclosed in my application Serial No. 731,760 filed April 29, 1958, now Patent No. 3,026,036 granted March 20, 1962.

It is a primary object of this invention to provide means considerably simplifying and strengthening the rotor construction while simultaneously greatly reducing the weight and size thereof and improving the safety of performance.

It is another object of the invention to provide means contributing to a highly efiicacious and economical turbine construction which is simple and easy to assemble and disassemble.

These and other objects and advantages of this present invention will become more apparent as the following description thereof progresses, which is illustrated in the attached 7 sheets of drawings, in which:

FIG. 1 is a horizontal section of the turbine pursuant to the invention in which the injection nozzles are located in two separate groups along the outer periphery.

FIG. 2 is a vertical sectional view of the turbine seen in FIG. 1.

FIG. 3 is a horizontal section of a modification of the turbine in which the injection nozzles are located only on one side along the outer periphery of the rotor.

FIG. 3a is a horizontal section of another form of the turbine, in which the injection nozzles are located in two opposite separate groups along the outer rotor periphery.

FIG. 4 is a fragmentary sectional view of a part of the rotor, the section being taken along line 4-4 of FIG. 5.

FIG. 4a is a fragmentary sectional view of a part of the rotor using tubes in place of blades.

'FIG. 5 is a perspective view of the rotor, portions of rotor top disc are cut out to facilitate inside view of the rotor for clarity sake.

FIG. 6 is a horizontal view of another modification, embodying injection nozzles located all around the outer periphery.

FIG. 7 is a vertical sectional view taken along lines 77 of FIG. 6.

Referring more particularly to the drawings, FIGS. 1, 2 and 3 illustrate preferred embodiments of the invention, in which the flow of power medium is guided in almost straight direction from nozzles 40 located in turbine housing 3 through power medium canals 17 into a rotatable inner guide body 4 or chamber 18a, also called guide body drum of rotor 1 as hereinafter in detail described.

In FIGURE 1 the performance of the power medium circulating through the rotor takes place in the following manner:

The power medium expelled from the nozzles located in two opposite groups around the outer rotor periphery circulating in opposite direction through the adjoining rotating gas canals 17 exerts in addition to impulse and pressure, also useful friction by action on the rotor in direction of rotation during passage through said gas canals 17.

The power medium expelled from said gas canals 17 into the rotating inner guide body 4, respectively, guide chamber 13a which is divided :by partition walls 5%, 53b to prevent whirl or eddy currents within guide pockets 52, 53 exerts again impulse by reaction on the rotor in rotating direction thereof, the power medium ejected from the inner guide body 4 into the inner canal ends of the remaining bypassing gas canals :17 exerting again impulse by pressure and useful friction by action on the rotor in rotating direction thereof during passage through said gas canals 17. The power medium expelled at the outer rotor periphery from said rotor gas canals 17 at its outer canal ends exerts again impulse by reaction similar to jet reaction on account of expansion, pressure, useful friction and centrifugal force on the rotor in rotating direction thereof.

The same performance of the circulating power medium takes place through both guide pockets 52., 53 of the guide body 4. Both ends of the cooling canals 19 are at the outer and inner rotor peripheries 1a, 1b sealed with respective plates 21a, 21b or other means against entry of power medium. Said gas canals 17 and cooling canals 19 are disposed in alternate sequence between both opposite arranged rotor discs 12a and 13a.

In FIGS. 2 and 7 it is shown that in the present invention the rotor consists only of one section constituted by rotor discs 12a and 13a in contrast to former disclosures of my inventions in which the rotor consists of 4 discs.

In FIG. 3 the working method is alike the one in FIG. 1, the only difference between these modifications is, that in FIG. 3, the nozzles are as shown located in one large group on one side along the outer rotor periphery, further that the fiow of gas expelled from said one group of nozzles is circulating in one direction through the rotor. The guide body 4 has no partition walls.

In FIG. 3a it is shown that the nozzles are also located in two opposite groups along the outer rotor periphery, or if preferred may also be disposed all around the outer rotor periphery 1:1 as can be seen in FIG. 6. The canals ends of the rotor cooling canals 19 are at the inner rotor periphery 1b sealed by plates 21:: or other means against entry of power medium from within the inner guide body 4. These rotor cooling canals 19 are at the outer rotor periphery 1a adjoining the nozzles 441' sealed with plates 21b or other means to prevent entry of power medium into said cooling canals 19 expelled from the nozzles.

The rotor gas canals 17 and the rotor cooling canals 19 are disposed in alternate sequence between both opposite arranged rotor discs. As in all other modifications, the respective portions of both rotor discs 12a, 13a form simultaneously the outer portions of the rotor gas canals 1'7 and the rotor cooling canals 19.

The outer portions of the rotor cooling canals 19 which constitute accordingly respective portions of both rotor discs 12a, 13a are provided near the inner rotor periphery 1b, with respective openings 19a for inlet of cooling air from the atmosphere on account of automatic suction taking place during rotation. Said rotor cooling canals 19 are provided near the outer rotor periphery 1a with openings 1% for outlet of said cooling air (FIGS. 1, 3, 3a).

The respective portions of said rotor discs 12a, 13a being respective portions of said rotor gas canals 1'7 and rotor cooling canals 1?, are in continuous contact with the ambient atmospheric air for cooling effect.

The flow of gas expelled from the nozzles into the rotor gas canals 17 is circulating therethrough radially in the direction of the inner rotor periphery 1b.

The inner guide body 4, respectively chamber 18a FIG. 3a between the inner rotor periphery 1b and the sleeve 34b surrounding shaft '2 is on one side in axial direction open for exhaust of gas, because the center portion of rotor disc 13a is eliminated in the same way as seen in rotor disc 13a of FIG. 7, while rotor disc 12a is closed by its center portion as seen in FIG. 2.

Said chamber 18a within the rotor center is separated by partition guide walls 52c, 52d, 53c, 53d (FIG. 3a), in order that the gas flow expelled from the nozzles 4%) into the adjoining gas canals 17 and from there into said chamber 18a is directed therefrom in axial direction into the open atmosphere.

The purpose of this peculiar arrangement according to FIG. 3a, designed for stationary turbines is to prevent re-entry of the power medium into the remaining opposite rotating gas canals 17 extending from the inner rotor periphery 11a towards the outer rotor periphery 1b in order to prevent passage of the power medium through, what would be then, a second turbine stage, further to achieve a longer cooling period for the hot rotor gas canals 17 before they receive the next charge of hot power medium. The present simplified new turbine rotor consists instead of three rotor sections in axial direction constituted of four rotor discs, as employed in my previous turbine inventions, only of a single rotor section, constituted of two rotor discs 12a, 13a, which formed in the previous turbines the rotor middle section, containing the rotor gas canals 17 and the rotor cooling canals 19 disposed in alternate sequence between said two rotor discs 12a, 13a (FIGS. 2, 5, 7).

As shown in my Patents Nos. 2,524,549 or 2,783,964 the two previously employed outer rotor cooling sections 0.8. have been eliminated in this present simplified new turbine rotor by removing the two outer rotor discs 12, 13 and further are eliminated the spaced rotor blades C, located between each of the two outer rotor cooling sections.

If preferred, the two outer gas trap sealing devices 24 at the outer rotor periphery (FIGS. 2 and 7) constituted by extensions 22 of rotor discs 12a, 13a and annular grooves located within housing 3, could also be eliminated and replaced with customary turbine sealing devices; noz- Zles 40 which are located within turbine housing 3 extend partially between extensions 22 of rotor discs 12a, 13a (FIGS. 2 and 7).

Said present simplified turbine rotor is constituted by said respective two opposite disposed rotor discs 12a, 13a which are secured to rotor shaft 2 in predetermined axial distance and which comprise therebetween spaced rotor blades C, constituting respective rotor power canals 17 and rotor cooling canals 19 (FIGS. 2, 5, 7).

Said rotor power or gas canals 17 and said cooling or air canals 19 are also called rotor power medium directing means, respectively rotor cooling medium directing means, and are accordingly constituted by said both opposite disposed rotor discs 120, 13a and the therebetween disposed spaced rotor blades C, defining conveying means, forming inner portions of said rotor canals 17 and 19 (FIGS. 2, 4a, 5 and 7).

Respective portions of said rotor discs constitute the outer parts of said cooling canals 19 of which each one as before described is provided near the inner rotor periphery 1b with openings 19a for inlet, and near the outer rotor periphery 1a with openings 1% for outlet (FIGS. 1, 3, 3a, 4, 6), or if preferred each cooling canal with one sufiicient large opening for inlet and outlet of said cooling medium (FIG. 4).

Sealing plates 21b are shown and indicated at the outer rotor periphery (FIG. 5) by dotted lines and sealing plates 21a and 21b at FIGS. 1, 3, 3a, 4 and 6 at the outer and inner rotor peripheries by hatched lines.

Power medium and cooling medium are each separately circulating through said respective rotor canals, constituting a rotating enclosure for flow of said respective power medium and cooling medium. Said rotating enclosure is revolving within a stationary turbine housing or casing 3 (FIGS. 1, 2, 3, 3a, 6 and 7).

The outer parts of rotor cooling canals and power medium canals being portions of both rotor discs 12a, 13a said outer parts respectively outer walls of rotor cooling canals 119 including said openings 19a, 1% which are in continuous direct contact with the ambient atmospheric air allowing by means of suction through openings 19::

near the inner rotor periphery entering of atmospheric air, which latter then is circulating along rotor blades C towards openings 1% near the outer rotor periphery 1a, cooling thereby very efliciently the side by side of the cooling canals 19 adjacent located gas canals 17, to be then expelled by means of expansion and centrifugal force through said openings 1% near the outer rotor periphery of said cooling canals 19 (FIGS. 1, 3, 3a, 4, 5 and 6). Both types of rotor canals extend from near the outer rotor periphery 1a to the inner rotor periphery 1b, the latter extends circumferentially in some distance from said shaft 2 (FIGS. 1, 3, 3a, 5, 6).

Within the inner rotor periphery 1b and the central sleeve 34b surrounding shaft 2 is provided between the opposite disposed rotor discs 12a, 13a by means of its center portions a rotatable chamber 18a defined by said rotatable inner guide body 4 (FIGS. 1, 2, 3, 3a, 6 and 7) which is modified in FIG. 1 by partition guide walls 52b, 53b in guide pockets 52, 53, constituting a first and second rotatable inner guide body section or if preferred be divided by more than one partition wall in two or more sections, respectively to form further guide pockets (not shown).

Said rotatable inner guide body 4 respectively chamber 18a is constituted by said center portions of the rotor discs 12a, 13a and the inner ends of the rotor blades C which terminate at the inner rotor periphery 1b (FIGS. 1, 2, 3, 3a, 6, 7).

In the modifications of FIGS. 1, 2, 3, 5 the center portions of rotor discs 12a, 12a are simultaneously parts of the rotatable inner guide body 4 or chamber 18a, further central sleeve 34b is protecting shaft 2 against direct heat contact, as well as protecting the rotor gas canals 17 against entry of cooling medium passing through cut outs 37 in the housing plates 6, 7 and orifices 14b in the rotor discs into and through said central sleeve 3% (FIGS. 2, 7 Said central sleeve 34b (FIGS. 2, 3, 3a, 6, 7) is fixedly connected with the center portions of said rotor discs 12a, 13a and in near distance surrounding shaft 2 and revolving therewith, which shaft '2 extends through and beyond rotor discs 12a, 13a (FIGS. 2, 7).

Ambient atmospheric air around the rotor discs 12a, 13a enters through said apertures 19a near the inner rotor periphery 1b provided in portions of each one of rotor discs 12a, 13:: being simultaneously portions of said rotor cooling canals 19 (FIGS. 1, 3, 3a, 4, 6). Said air is entering through said apertures 19a into said cooling canals 19 and after passing therethrough is expelled out into the atmosphere on account of centrifugal force and expansion through apertures 1% near the outer rotor periphery 1a provided within said rotor discs 12a, 13a, respectively within said rotor cooling canals. If instead rotor blades C located within rotor discs 12a, 13a rotor tubes are ernployed (FIG. 46:), not only saidrotor discs themselves, but also the inserted rotor tubes are each to be provided at the corresponding positions on both opposite portions with at least one substantially large aperture for circulation of cooling medium.

Referring particularly to FIG. 4 details shown therein are as follows: One of said rotor cooling canals 19 has two apertures 19a, 1%, whereas the other right hand cooling canal 19 has only a simple large aperture extending from near one canal end to near the other canal end.

FIG. 5 is a perspective view of the present improved turbine rotor including rotor power canals 17 open at both ends and rotor cooling canals 19, covered by plates 21b 0 other means indicated by clotted lines. Portions of one rotor disc are cut out to facilitate for claritys sake inside view of the rotor.

Between rotor discs 12a, 13b are as before mentioned, spaced rotor blades C, forming jointly cooling medium canals and power medium canals, constituting together simultaneously a revolving enclosure, respectively casing. Within the respective rotor canals, power medium and cooling medium are separately circulating in enclosed condition, and are revolving within the stationary housing 3 (FIGS. 1, 3, 3a and 6).

Performance, proceedings and eifects of the power medium, as well as the circulation thereof during operation, also the other features within the present new rotor pursuant to (FIGS. 1, 2, 3, 3a, 6, 7) are carried out and taking place in the same way as described in application Serial No. 731,760, now Patent No. 3,026,086, but with greater efficiency on account of the much lighter weight, direct supply of large masses of atmospheric air and other advantages.

Performance, proceedings and effects of the cooling medium in the present new embodiment takes place in almost the same manner and way, as described in application Serial No. 731,760, now Patent No. 3,026,086, with the only exception of variation of the air circulation, because in the present new simplified rotor construction no rotor outer air cooling section 0.8. are present, but only a single rotor section including power and cooling air canals disposed in alternate sequence, so that the surrounding ambient air around the rotor discs 12a, 13a enters through openings 19a near the inner rotor periphery 1b direct into the rotor cooling canals 19 (FIGS. 1, 3, 3a, 4, 5, 6) instead indirectly by means of said both rotor outer air cooling sections 0.5. as previously disclosed in my aforesaid applications.

The outer walls of the rotor power canals 17 as well as of the rotor cooling canals 19 being portions of the rotor discs 12a, 13a are very efficiently cooled on account of the high rotor revolution, during which the rotor discs with said openings 19a, 1% are cutting through the surrounding ambient atmospheric air, while in the former rotor modification as shown in my Patents Nos. 2,524,549 or 2,783,964, atmospheric air enters via said openings 19a into said cooling canals 19 within the middle rotor section indirect from the rotor cooling canals 19 located within said both outer rotor cooling sections O.S.

In consequence of the peculiarly arranged rotor construction, there is no harmful friction of the power medium and the cooling medium with the stationary turbine housing or casing, because the respective circulating media enclosed in the rotor canal do not come in contact therewith, neither develops harmful friction with the rotor canals. On the contrary there is only as before mentioned useful friction in direction of rotation of both circulating media with the rotor canal walls, thereby increasing the driving force, respectively the turbine power output. Therefore very small and insignificant power output is lost in spite of air suction and air expulsion of huge masses of cooling air circulating during rapid revolution of the turbine rotor, but is in three ways almost fully compensated for, first by impact (action) of the vigorous onrushing air flow entering via openings 37 provided in the housing plates 6, 7 (FIGS. 2, 7) and via opening 1% near the inner rotor periphery in rotor discs 12a, 13a against the peculiar curved rotor blades C (FIGS. 1, 3, 3a, 5, 6), secondly by impulse and pressure during the enormous rapid passage of the cooling air through the rotor cooling canals 19 and thirdly by repulsion (reaction of the air flow when expelled with great contrifugal force from the cooling canals 19 at the outer rotor periphery 1a (FIGS. 1, 2, 3, 3a, 4, 5, 6).

The onrushing air flow against the rotor blades C, respectively rotor canals is working in a similar manner as the wind striking against the blades of a wind mill.

To increase the efiiciency of cooling the hot rotor power canals 17, freezers, air conditioners or other cooling means (not shown) may be arranged at opposite sides, between the housing plates 6 and 7 and the rotor 1, as shown in the application Serial No. 731,760 filed April 29, 1958.

The rotor power canals or tubes 17 and the rotor cooling canals or tubes 19 are curved, forming preferably a part of an absolute or an approximate logarithmic spiral. Said rotor canals are curved in the direction of the rotor movement and curved at opposed ends; these curvatures at opposed ends are situated with respect to the inner and outer rotor peripheries in an angle somewhat opposed to the direction of rotor movement.

In the present instance the rotor canals, tubes or the like are substantially oblong and the profile of the gas canals or tubes have throughout their entire length the same square measurement in order to ensure equal flow of power medium.

Due to the fact, that the power and cooling media are simultaneously moving in enclosed condition, while passing through the respective revolving rotor canals 17, 19 within the turbine casing, contact and detriment-a1 friction of the power as well as of the cooling medium with the walls of the stationary turbine casing 3 during their circulation through the turbine rotor canals is effectively almost entirely eliminated.

To achieve the aforesaid and other purposes, the turbine according to my Patent No. 2,524,549 issued October 3, 0, has been improved pursuant to the present invention and greatly simplified by eliminating all outer guide pockets, the numerous guide members of the inner guide pockets, the inner rotor rim members, the inner stationary guide body being replaced by an inner rotating guide body, the stationary sleeve being replaced by a rotating sleeve. Further there are eliminated the sleeve support, some ball-bearings, the inner gas trap sealing devices, constituted by the inner rotor disc extensions and the annular grooves provided within the inner stationary .guide body.

Further eliminated are the two outer rotor discs 12 and 13 and all rotor blades respectively rotor air cooling canals disposed between rotor discs 12 and 12b, and 13- and 13b, constituting the rotor cooling canals located within both outer rotor cooling sections.

FIGS. 6 and 7 illustrate a modification pursuant the invention for use in airplanes.

Rotor 200 has an open chamber 18a between the inner rotor periphery and the central sleeve 34b (FIGS. 6, 7) to allow axial passage therethrough of atmospheric air rammed into by means of the airplane nose during forward flight, as well as to allow exhaust gas ejected from the gas canals 17 running into said open chamber disposed in alternate sequence with the rotor air cooling canals within the single rotor section, being in my previous disclosures the rotor middle section. Said cooling canals 19 are sealed at opposed ends to prevent entrance of power medium.

The radially extending rotor gas canals 17 are beyond the inner rotor periphery 1b somewhat extending in axial curved direction into said rotor chamber 18a towards the plane tail (FIG. 6).

The center portions of rotor discs 12a, 13a, as well as the housing plates 6, 7 have according modification FIGS. 6, 7 large cut outs to provide openings 37, 14a, 14b to allow abundant air inlet and air and gas outlets according to arrows A and G (FIG. 7).

In FIG. 6 the center portions within the inner rotor periphery 1b of either or both rotor discs 12a, 13a may be eliminated, depending whether the turbine is used for stationary purposes or for airplanes.

The swift circulating air through the cooling canals 19 are efficiently cooling the adjacent hot Walls of the power medium canals 17, respectively, the rotor blades C.

Said power medium rotor canals 17 being entirely surrounded by cooling means, that is partly by the adjacent cooling canals and partly by the ambient atmospheric air surrounding the rotor discs 12a, 13a.

The construction of the cooling system and the method of cooling proceedings are in the present modifications identical with the turbine modifications previously disclosed.

The rotor chamber 18a is pursuant to modification FIGS. 6, 7 not sealed off by the center portions of rotor discs 12a, 13a, which form in the modifications of FIGS.

2 and 3 portions of the axially sealed rotating inner guide body 4 or chamber 18a intended for radial passage of power medium.

Inmodification (FIGS. 6, 7) said rotor chamber 18a is used for axial passage of the exhaust gas injected thereintd from the power canals 17 together with the atmospheric air rammed into said airplane nose, to be jointly expelled with great force through the tail end of the airplane, adding considerable turbine power output by jetreaction.

In the modification of FIGS. 6, 7, the injection nozzles 40 are disposed all around the entire outer rotor periphery.

On account of the various elirninations and the specific rotor construction, undesirable harmful friction is very insignificant, further because of the greatly simplified construction, the turbine is considerably reduced in size and'weight and the safety of performance is very improved.

Means may be provided to overcome various difficulties arising from different peculiarities of the rotor material used, as are: strain, stress, pull, tension, creep, thermal expansion in consequence of the high temperatures of the power medium and the enormous rotor revolution.

Means to overcome said difliculties, are to assemble interchangeably the separate important rotor parts, such as the rotor discs, rotor blades, strips or tubes and other parts, for instance with: threaded bolts 10% passing through and beyond the repective rotor discs at such places which are not in direct contact with the hot gases.

Said rotor discs are secured to said threaded bolts 1% by nuts 101 pressing against very strong special springs 102 or compressed air cushions or other elastic, selfadjusting shock and pressure resisting means, permitting expansion and contraction of the rotor material, in such a manner, that all assembled rotor parts form a compact structure, safely withstanding the high centrifugal force caused by the enormous rotor speed, and all other mentioned forces and ditficulties (FIG. 5).

This new method of assembling, mounting and dismounting of rotors exchange of rotor parts, repairs, cleaning as well as re-assembling of rotors is most simple and accomplished in much less time as usual, for instance by welding, soldering, etc.

The turbine housing, as well as the rotor and its various parts of all mentioned modifications, may if preferred, each be constructed as a unit from a casting, or in secrtions made of castings to facilitate assembling of the turbine.

If not detrimental to the compactness, tear-pull and strain resistance required of the rotor material on account of said specified difficulties and forces, for the purpose of furtherimprovements of the cooling capacity, porous rotor material or such with tiny slots may be used, to enable besides convection also transpiration or film cooling.

The number of power canals 17 and cooling canals 19 may vary and and their shapes are preferably oblong.

Number and proportions of dimensions of nozzles, rotor canals, dimensions of the innerguide body, guide pockets, the open space respectively chamber of the rotor have to be each calculated respectively adapted in conformity with the quantity, pressure and other characteristics of the power medium used in the turbine and the necessities of the power capacity desired, respectively required.

It is well understood in accordance with the above description and drawings submitted, that deviations and changes may be made from the embodiments herein set forth, without departing from the spirit and scope of this invention.

Having thus described the invention, what is claimed as new and desired to be secured by Letters Patent, is:

-l. A rotor structure for a turbine comprising two parallel and spaced rotor discs having therebetween a plurality of rotor blades, which are spaced from each other and extend in substantially radial direction from the outer periphery to the inner rotor periphery and in axial direction from'one of the rotor discs to the other rotor disc, said blades defining power medium rotor canals terminating in open ends located at the outer rotor periphery and at the inner rotor periphery, respectively, said power medium rotor canals being spaced from each other and defining therebetween cooling medium rotor canals provided with opposite sealed ends at the inner and outer rotor periphery respectively, said cooling medium rotor canals having openings constituting an inlet opening for a cooling medium located near the inner rotor periphery and an outlet opening for said cooling medium located near the outer rotor periphery, said cooling medium rotor canals communicating directly with the atmosphere through said openings in said rotor discs.

2. A rotor structure for a turbine comprising two parallel spaced ring-shaped rotor discs having an inner rotor periphery and an outer rotor periphery, a sleeve member, power medium rotor manals and cooling medium rotor canals located in alternate sequence between and defined by said parallel spaced rotor discs, said power medium rotor canals and said cooling medium rotor canals extending from said inner rotor periphery to said outer rotor periphery of said rotor discs, said inner rotor pe riphery and said sleeve member forming the boundary of a chamber having one open end located in one of said ring shaped rotor discs and being closed at the face of the other rotor disc and centrally located guide walls within said chamber and extending from one side to the opposite side of said inner rotor periphery, said guide Walls facilitating expulsion of combustion gas in axial direction of said one rotor disc when the gas passes said chamber from said power medium rotor canals.

3. A rotor structure for a turbine comprising two spaced parallel ring shaped rotor discs having an inner rotor periphery and an outer roto periphery, a sleeve extending axially and centrally through said discs, radially directed power medium rotor canals and cooling medium rotor canals located in alternate sequential relationship between said rotor discs, a chamber bounded by said sleeve and said inner rotor periphery and being open at both said rotor discs, said cooling medium rotor canals and said power medium rotor canals extending from said outer rotor periphery to said inner rotor periphery and projecting therefrom into said chamber.

References Cited in the file of this patent UNITED STATES PATENTS 1,887,717 Koch Nov. 15, 1932 2,524,549 Theimer Oct. 3, 1950 2,568,726 Franz Sept. 25, 1951 2,641,040 Goddard June 9, 1953 2,783,964 Theimer Mar. 5, 1957

Claims (1)

1. A ROTOR STRUCTURE FOR A TURBINE COMPRISING TWO PARALLEL AND SPACED ROTOR DISCS HAVING THEREBETWEEN A PLURALITY OF ROTOR BLADES, WHICH ARE SPACED FROM EACH OTHER AND EXTEND IN SUBSTANTIALLY RADIAL DIRECTION FROM THE OUTER PERIPHERY TO THE INNER ROTOR PERIPHERY AND IN AXIAL DIRECTION FROM ONE OF THE ROTOR DISCS TO THE OTHER ROTOR DISC, SAID BLADES DEFINING POWER MEDIUM ROTOR CANALS TERMINATING IN OPEN ENDS LOCATED AT THE OUTER ROTOR PERIPHERY AND AT THE INNER ROTOR PERIPHERY, RESPECTIVELY, SAID POWER MEDIUM ROTOR CANALS BEING SPACED FROM EACH OTHER AND DEFINING THEREBETWEEN COOLING MEDIUM ROTOR CANALS PROVIDED WITH OPPOSITE SEALED ENDS AT THE INNER AND OUTER ROTOR PERIPHERY RESPECTIVELY, SAID COOLING MEDIUM ROTOR CANALS HAVING OPENINGS CONSTITUTING AN INLET OPENING FOR A COOLING MEDIUM LOCATED NEAR THE INNER ROTOR PERIPHERY AND AN OUTLET OPENING FOR SAID COOLING MEDIUM LOCATED NEAR THE OUTER ROTOR PERIPHERY, SAID COOLING MEDIUM ROTOR CANALS COMMUNICATING DIRECTLY WITH THE ATMOSPHERE THROUGH SAID OPENINGS IN SAID ROTOR DISCS.

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