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2,592,227 5 ,6 cooling the rotor and for reducing the tempera ture at which the parts operate in order to re duce the corrosion of the parts of the turbine. When operating with steam, the latter is ad mitted under appropriate pressure through the openings 21 and the blades or vanes 29 may be omitted. No steam is then admitted into the interior of the turbine rotor. I shape and are arranged in rows around the blade carrier I00. The air is drawn in between the ribs 99 and is driven by blades I06 towards the rear end of the casing being more and more compressed during this?ow. When theairreachesthechamber I08 on the rear of the casing, which may be pro vided with radial ribs I09, its direction of flow is reversed (as shown by the arrow) and it is Figures 6 to 13 show another modi?cation of the turbine which is designed for explosive gases 10 now driven by blades I01 towards the front end, which have to be mixed with air. In this modi?cation the shaft 22 and the ro tor 2| are substantially identical with the cor beingcompressedontheway. It?nallyisdis charged over the collar I05 into the combustion chamber; ithas acquired a high pressure during the process and itmay therefore be used in con responding parts of the modi?cation as above described. They need not be described in de 15 nection with heavy fuel oils which are injected tail. Thecasing,however,isofadifferentcon struction. - through pipes 3|. In other respects, the turbine will operate like the modi?cation shown in Figures 1 to 5. It will be seen from the above that the turbine pressor and with an inner section 9| housing 20 according to the invention is an action-reaction Y As seen in Figure 6, the casing is provided with an outer section 90 housing an air com the rotor. The inner section 9I in this modi cation is conical and has a smooth inner sur face. The channels of the reaction section of the casing are formed by separate rings 93, 94, 95, 96 which are ?xedly mounted within said conical surface and may be held ?rmly by ap propriate means such as screws (not shown) and by caulking after having been ?tted prop erly. Thesaidrings93,94,95,96maybepro vided with blades 91, as clearly seen in Figure 13, sub-dividing the gas stream and producing the desired jet effect. The cylindrical sleeve inserted between‘ the casing and the rotor, such as shown in the modi?cation illustrated in Fig ure4,canthereforebedispensedwith. The35cision. , “ - . rings may be relatively short with an arcuate inner surface covering an arc of only 90°. On the outside the conical part 9I of the casingpresentsasteppedappearance. Itforms theinnersurfaceofamulti-stagerotarycom 40 pressor which provides the combustion cham ber 28 with compressed air. The examples described show a de?nite direc tion of rotation, which may be reversed, as well known, by reversing the position of the blades and jet openings with respect to the shaft. I claim: , 1.A multistage turbine for operation with elastic ?uids passing through the turbine in a combined axial and radial flow, comprising a rotor with a cylindrical outer surface, provided stepped on the inside. This outer casing 90 4.5witha series of juxtaposed radially extending The said multi-stage compressor is enclosed in v a casing 90 of conical shape which may be is ?xed to the turbine casing by means of a large number of radial ribs or spokes 98 (Figure 9) holding a ring 99 which is V-shaped and sur rounds the combustion chamber 28; said ring is closed by the front wall I0I. The rear part of the outer casing 90 is joined to the inner casing 92' and to the rear wall I02 of the casing by a ring I03. circumferential grooves of substantially semi circular cross section of increasing width and depth in the direction of axial flow, blades ar ranged within said grooves inclined tangentially 50 and axially, so that a line proceeding along the blade towards the axis of the cylindrical surface is inclined with respect to a radial plane passing through said axis and a line running along the blade in an axial direction is inclined with re In the space between the two members 99 and 9| the rotor of the compressor is inserted 55 spect to the elements of the cylinder, a stator which comprises a conical blade carrier I00 ?xed to the front wall 30 of the rotor 2| by a num ber of ribs I04 between which the gases may enter from the combustion chamber into the rotor. The ribs I04 carry a ring I95 which 60 in the direction of flow, acting as ?ow direction , forms a projecting dish-like collar guiding the compressed air which is discharged by the com pressor into the combustion chamber. reversing chambers, the grooves in the rotor and stator being staggered and a flow dividing cyl inder, arranged between the cylindrical surfaces of the rotor and the stator, provided with inlet The blade carrier I00 carries two series of blades I06 and I0‘! one at the inside and one 65 and outlet openings, the former subdividing the at the outside. The outer set I06 diminishes in size from the front end to the rear end of the casing in accordance with the increasing pressure while the second set I01 decreases in size from the rear side to the front side. A 70 plan view of a strip of the blade carrier I09 with blades I06 arranged at the outside of the carrier is shown in Figure 7, while a similar circumferential continuous radial flow of the ?uid emerging from the flow reversing circumferential grooves of the stator into a number of separate jets. 2.A multistage turbine for operation with elastic ?uids passing through the turbine in a combined axial and radial flow, comprising a rotor with a cylindrical outer surface, provided with a series of juxtaposed radially extending strip showing the blades on the inside is shown in Figure 8. The blades have any well-known 75 circumferential grooves of substantially semi turbine combining the advantages of the tan gential ?ow turbine with those of the axial flow turbine. It will also be seen that the turbine may have any size; itmay merely have the size of a motor driving a tool or the like, a feature whichisofgreatadvantage. Theconstruction is moreover such that a minimum of distortion under the high temperatures will occur/V "The jet effect produced in each stage allows a certain amount of clearance and a certain amount of distortion may even take place’without binding between the moving and the’stationary parts. It will moreover be noted that all the parts used may be easily/machined with great pre with a cylindrical inner surface provided with a series of juxtaposed radially extending circum ferential grooves of substantially semi-circular cross section, of a width and depth increasingPDF Image | COMBINED RADIAL AND AXIAL FLOW MULTISTAGE TURBINE
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