US2979305A

US2979305A - Turbine with funnel drive vanes

Info

Publication number: US2979305A
Application number: US662918A
Authority: US
Inventors: Kwiatek Stanislaw
Original assignee: Individual
Current assignee: Individual
Priority date: 1957-05-31
Filing date: 1957-05-31
Publication date: 1961-04-11
Anticipated expiration: 1978-04-11

Description

April 11, 1961 s. KWIATEK TURBINE WITH FUNNEL DRIVE VANES 3 Sheet-Sheet 1 Filed May 31, 1957 Slan/s/ow Km'afe/r INVENTOR. 406?.

BY M

April 11, 1961 s.1 w|A'rEK 2,979,305

TURBINE WITH FUNNEL DRIVE VANES Filed May 31, 1957 3 Sheets-Sheet 2 V "3 V IN VEN TOR.

24 BY V MMZ5% April 1961 5. KWIATEK 2,979,305

TURBINE WITH FUNNEL DRIVE VANES Filed May 51, 1957 3 Sheets-Sheet 3 Slams/aw Kw/a/e/r INVENTOR.

Y W WQW,

United States Patent 2,919,305 TURBINE WITH FUNNEL DRIVE VANES Stanislaw Kwiatek, 13812 Linn Ave, Cleveland 25, Ohio Filed May 31, 1951, Ser. No. 662,918

2 Claims. (Cl. 253 -48) The present invention generally relates to a turbine construction and more particularly to a turbine including a rotary compressor for supplying compressed air together with fuel means for providing a combustible mixture to a combustion chamber with the combustion chamber discharging onto the vanes or buckets on a rotatable disk with the disk being secured to a power shaft for causing the power shaft to rotate due to movement of the gases towards a discharge opening and the drag of the gases on the blade or pocket on the turbine disk.

An object of the present invention is to provide a turbine construction in accordance with the preceding in which the pockets are generally frusto-conical in shape thus generally defining funnel-shaped pockets for receiving the expanding products of combustion from the combustion chamber and converting these products into useful work by rotating a power shaft.

Another important object of the present invention is to provide a multi-stage turbine in which the first stage is employed for driving an air compressor with the second and third stages being the power stages of the turbine.

Yet another important feature of the present invention is its simplicity of construction, ease of operation, efliciency, ease of assembly and disassembly and its relatively inexpensive manufacturing cost.

These together with other objects and advantages which will become subsequently apparent reside in the details of construction and operation as morefully hereinafter described and claimed, reference being had to the accompanying drawings forming a part hereof, wherein like numerals refer to like parts throughout, and in which:

Figure 1 is a perspective view of the turbine of the present invention;

Figure 2 is a longitudinal, vertical sectional view taken substantially upon a plane passing along section line 2-2 of Figure 1 showing the internal structural details of the turbine;

Figure 3 is a transverse, vertical sectionalview taken substantially along the line of separation of, the casing at the first stage of the turbine;

Figure 4 is a schematic view showing the path of the combustion products through the several stages of the turbineyand a Figure 5 is a detailed sectional view taken substantially upon a plane passing along section line 5-5 of Figure 2illustrating the orientation of the shafts for the first stage of the turbine and the second and third stage ofthe turbine. l

1 Referring now specifically to the drawings, the numeral 10 generally designates the turbine of the present invention which includes an elongated generally cylindrical housing .12divided intoa plurality of cylindrical'sections designated by

numerals

14, 16, 18 and 22. These sec tions are all interconnected by virtue of peripheral flanges 24 at the adjacent ends thereof with fastening bolts 26 extending therethrough for securing the sections in position- Each of,the

sections

14, 16, 18 and 22 is provided with a centrally disposed cylindrical bore 28. Secured 2,979,305 Patented Apr. 11, 1961 to the section 14 is a throat or inlet section 30 having an open end 32 forming an air intake for a rotating com pressor impeller 34 mounted within the section 30 and rotatable with a power shaft 36 for discharging air tangentially into a discharge conduit 38 whichin turn discharges into a combustion chamber generally designated by numeral 40 with a fuel supply'line 42 being connected with the conduit 38 immediately at the inlet of the combustion chamber 40 which is in the form of curved cylindrical member 44 having a cylindrical bafile 46 mounted therein in spaced relation thereto with the baflle 46 having openings 48 therein. The open ends of the curved and generally cylindrical baffle correspond with the open ends of the combustion chamber and the fuel line 42 extends inwardly into the interior of the baffle 46 and is supported by a bracket 50 therein with the discharge nozzle 52 being disposed in the bafile or burning area defined by baffle 46 so that a flame'may be produced therein for discharging from the combustion chamber 40. V 1

The section 30 is secured to the section 14 by virtue of a peripheral flange 54 and fastening bolts 56. Also, the discharge conduit 38 is provided with a flange 58 for engagement with a flange 60 on the section 30 with fastening bolts 62 extendingtherethrough for detachablyconnecting the conduit 38, with the section 30 thus mounting the combustion chamber 40 in the desired area.

Each of the

sections

14, 16, 18 and 22 is hollow and provided with sealed water compartments 64 each of which is provided with a water inlet line 66 and a water outlet line 68 for connection with a suitable source of cooling water. The facing surfaces of the sections. are each provided with an annular recess 70 which generally defines a cylindrical outline when the facing recesses are brought into adjacent relation as when the device is assembled. The annular facing recesses 70 coact to form an annular passage for permitting rotation of a turbine disk 72 having a plurality of buckets 74 mounted on the periphery thereof in circumferentially spaced relation with each of the buckets being substantially frustoconicalin shape and being open at each end thereof with the large end facing away from the direction of rotation and the small end facing the direction of rotation wherein the buckets or pockets 74 generally arefunnel-shaped. As clearly seen in Figure 3, there are three stages to the turbine of the present invention and each of the stages is substantially identical as to the disk 72 and the buckets 74 and their relationship to the annular passage formed by the recesses or grooves-70. The combustion chamber 44 is provided with a flange 76 for attachment to the juncture between the sections 14 and 16 by fastening bolts 78 thereby retaining the combustion chambers 44 telescoped into an inlet opening 80 in the junctional area between the sections 14 and 16 for supplying hot combustion products into the passage 70 and into en gagement with the large end of the buckets 74. whereby the expanding gases will go through the bucket 74 with the velocity force or break awayf force causing the gases to drag the bucket 74 with them for overcoming any reaction force and thus causing the disk 72 to rotate;

After the combustion gases have passed for approximately they are discharged through a discharge opening'82 in the junctural area between the sections 14 and 16 with an exhaust pipe 84 being connected thereto by fastening bolts 86. The exhaust pipe 84 is generally -U-shaped as shown in Figure l and forms an inletfor thesecond' stage of the turbine wherein the hot and expanding combustion gases will be utilized for driving the second stage of the turbine and the gases will then be discharged into the third stage of the turbine for utilization of any remaining energy therein. Each stage of the turbine operates in substantially the same manner in that amazes the combustion products impinging upon and passing through the funnel-shaped buckets will cause drag to cause rotation of the disk. The combustion bases are in the first stage of the turbine for substantially 140, are in the second stage of the turbine for approximately 145 and in the third stage of the turbine for approximately 160 of rotation.

The disk 72 of the first turbine stage is provided with a hollow shaft 88 received in the longitudinal bore 28. The hollow shaft 88 is provided with a reduced portion 90 integral with and forming a continuation of the mounting shaft 36 for the compressor impeller 34. The reduced portion 90 of the shaft 88 is journaled in ball bearings 92 and provided with an oil seal 94 disposed exteriorly thereof. 'A closure flange 96 is provided against the outer surface of the oil seal 94 and is detachably connected to the section 14 by fastening screws 98 thus forming a keeper and assisting in the operation of the oil seal 94 and preventing leakage of excessive oil into the compressor. The hollow shaft 88 is provided with an elongated longitudinal bore 100 extending inwardly from the inner end thereof. Each of the disks 72 of the second and third stages of the turbine are provided with a central hub 102 secured to a central power shaft 104 which has a reduced longitudinally extending portion 106 received within the bore 100 and journaled therein by ball bearings 108 with an oil seal 110 being providing for assuring lubrication of the bearings 108. The shaft 104 is provided with a peripheral flange 112 forming an abutment for the inner ends of the hubs 102 and being provided with a longitudinally extending sealing flange 114 engaging in a groove in the end of the hollow shaft 88 thus adding an additional seal for the bearings 108 to prevent escape of lubrication and to prevent entry of gases into the bearings. The other end of the shaft 104 is provided skilled in the art, it is not desired to limit the invention to the exact construction and operation shown and dewith a threaded portion 116 having a clamp nut 118 thereon for rigidly securing the hubs 102 onto the shaft 104. A lubrication seal 120 is disposed immediately outwardly of the screw threaded portion 116 and ball bearings 122 support this portion of the shaft 104 and the section 22 of the casing 12. A lubrication seal 124 is disposed at the outer end of a flange 126 disposed in the longitudinal bore 28 thus providing an oil chamber for receiving oil from a radial passageway 128 communicated with an oil supply line 130 whereby oil may be supplied within the chamber between the lubrication seal 124 and the ball bearings 122 as well as the lubrication seal 120. The shaft 104 is provided with a longitudinal passageway 132 having a radial portion 134 communicating with the oil reservoir together with a discharge radially extending opening 134 for lubricating thespaced ball bearings 108 which are retained in spaced relation by a spacer sleeve 136. The reduced portion of the shaft 88 is provided with a passageway 138 terminating in an angularly extending portion 140 for communicating the oil passageway with the lubrication seal 94. It is noted that the inner end of the reduced portion 106 is spaced from the inner end of the bore 100 but the lubrication will still go into the bore or passageway 138 due to the construction of the ball bearings 108 which form a partial seal and also the lubrication seal 110. The outer free end of the shaft 104 is provided with a tapered portion 142 terminating in a screw threaded hub or attaching member 144 for engagement with any power source for driving the same whereby the device will act as a power unit.

From the foregoing description, it will readily be apparent that the initial stage of the turbine is employed scribed, and accordingly, all suitable modifications and changes will be resorted to, falling within the scope of the invention as claimed.

. What is claimed as new is as follows:

'1. A multi-stage turbine comprising a plurality of aligned annular chambers with the inner peripheries thereof defining a longitudinal passage, a power shaft rotatably supported within the longitudinal passage, a plurality of disc rotors mounted on said power shaft with the inner periphery of each annular chamber having a slot receiving the periphery of a disc rotor, and a plurality of circumferentially spaced vanes rigidly mounted on the periphery of each rotor and having a cross-sectional area only slightly less than the cross-sectional area of the interior of the annular chamber, each annular chamber having an intake communicated therewith and a discharge spaced circumferentially from the intake, the intake of the first annular chamber receiving combustion products from a source of supply, the intake of succeeding annular chamhere being communicated with the discharge from the immediately preceding annular chamber, the discharge of the last annular chamber being communicated with the atmosphere, each of said vanes having a passage extending therethrough with the crosssectional area of the passage being less than the cross-sectional area of the annular chamber for permitting passage of a portion of the combustion products through the vane into contact with the adjacent vane on the same disc located nearer to the discharge.

2. The turbine as defined in claim 1 wherein each of said vane is generally funnel-shaped in configuration having the smaller end thereof forming the passage and having the larger end facing the intake when the vane is disposed between the intake and discharge for receiving combustion products from the intake or a succeeding vane, the longitudinal axis of the funnel-shaped vane being disposed generally in acute angular relation to a radius of the rotor intersecting the outermost forward edge of the vane with the acute angle being disposed on the side of such a radius in the direction of rotation.