US1310673A - Turbine-casing - Google Patents

Description

E. H. SHEBBONDY.

TURBINE CASING.

APPLICATION FILED MAR. 26. I918.

Patented July 22, 1919.

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E. H. SHERBONDY.

TURBINE CASI'NG.

APPLICATION FILED MAR. 26. I918.

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TURBINE CASING.

APPLICATION FILED MAR. 26, I918.

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UNITED STATES PA @FTQ.

EARL H. SHERBONDY, OF CLEVELAND, OHIO.

TURBINE-CASING.

I Specification of Letters Patent.

Patented July 22, 1919.

' Application filed March 26, 1918. Serial No. 224,892.

T 0 all whom it may concern:

Be it known that I, EARL H. SHERBONDY, a citizen of the United States, and resident of Cleveland, in the county of Cuyahoga and State of Ohio, have invented a certain new and useful Turbine-Casing, of which the following is a specification.

This invention relates to a casing for a turbine, more particularly, a turbine that is actuated by the exhaust gases from an internal combustion engine.

The turbine is intended to be actuated by the exhaust gases from an airplane engine and is intended to operate a centrifugal blower fan, as more specifically described-in my application, Serial No. 224,356, filed March 23, 1918.

Such turbine casing, on. account of the hmitations of space in an airplane fuselage, must be as small and as light as possible. Another important object to be kept in mind, is to design a casing which consists of a few simple parts so designed that the main parts can be readily stamped out of sheet metal, whereby the casing unit may be readily produced in large quantities.

This invention is intended to fulfil the above-mentioned conditions and also pre- Figure 1 is a side elevation partly in section of the casin as a whole; Fig. 2 is an end view, partly broken away for clearness, looking from the right of Fig. 1; Fig. 3 is a sectional view, on an enlarged scale, taken on the line 33 of Fig. 2; Fig. 4 is an end view, looking from the left of Fig. 1; Fig. 5 shows a development of the nozzle and turbine buckets; Fig. 6 is a side view of a modified arrangement, partly in section; Fig. 7 is an end view of the same; Fig. 8 is a view of the engine to which the modified form, shown in Fig.6, is applied; Fig. 9 is a sectional View, on an enlarged scale, taken on the line 99 of 6; and Fig. 10 is a section on line 10--10 of Fig. 6.

Referring now to the drawings, in which similar reference characters, indicate similar parts in the different figures, 1 is the turbine provided with the usual buckets 2 mounted on the shaft 3, which in turn, is mounted in the bearings 4 and 5.

The turbine casing consists essentially of three parts. A main casing element designated 7 is shaped substantially like a shallow dish-pan and provided with an annular flange 8 and the base portion 9. The shaft 3 passes through the center of the base 9. The base 9 is provided with two or more inlet ports 10 and the side wall of said casing element 7 is provided with two or more exhaust ports 11. Inlet pipes 12 which will 0bviously be connected to the exhaust manifolds of the engine register with the ports 10 and the exhaust pipes 13 register with the ports 11.

The second element of the casing, is a back plate 14, which is annular in shape, is flanged at its outer periphery and joined in any suitable manner to the flange 8 of the casing 7 and toward its inner periphery, is bent in toward the turbine 1, so that a. curved path is provided for the gases as they leave the buckets 2 of the turbine. The inner annularedge 14 is indicated at 15.

The third element of the casing, is the annular diaphragm 16, which is arranged between the casing elements 7 and 14 and between the inlet and exhaust ports 10 and 11 respectively, so that the interior of the easing is divided into an inlet chamber 17 and an exhaust chamber 18.

The diaphragm 16 is substantially conical in section and is flanged at its outer periphery, so as to make -a tight fit, as at the point 19 with the side wall of the casing 7, the point 19 being located between the ports 10 and 11. l

The inner periphery of the diaphragm 16 is seated tightly against a nozzle ring 20 and held there by the ring 20', which nozzle ring presents a series of nozzles 21', as shown in Fig. 2. An annular element 22 is attached to the opposite side of the nozzle ring 20 at one end and is attached to the base portion 9 of the casing 7 as indicated at thus completing the inlet chamber 17. This nozzle ring is shown more specifically in my copending application, Serial No. 227,331. filed April 8. 1918. The course of the gases is indicated by the arrows, the gases entering through the pipes 12, being guided by the diaphragm 16 through the nozzle ring 20, thence to the buckets 2 of the turbine, thence into the exhaust chamber 18 and out through the exhaust pipes 13.

Attention is particularly directed to the simplicit in shape of the main casing element 7, t e back plate 14 and the diaphragm 16. These elements can readily be stamped out of sheet metal, can be readily welded or riveted together, as desired and so a design of the gasses, is to reduce the speed of the turbine. One, or more, holes 24 are cut through the diaphragm 16 and a cylindrical element 25 flanged as at 26, is arranged around the edge of this hole as-shown. The

other end of this cylindrical element 25 is arranged, as at 27, to seat the valve 28. This valve may be controlled'in any desired manner, such as, for example, by the means shown in my application, Serial No. 224,894, filed March 26, 1918. These holes 24 are preferably arranged about half way between the inlet ports 10 as shown in Fig. 2. A suitable packing gland 29 may be provided for the valve stem.

Attention is called to the arrangement of the exhaust pipes and by-pass valves, whereby the same exhaust pipe functions to carry the actuating fluid away from the turbine, whether said fluid has been caused topass through the turbine buckets, orwhether it has been by-passed'through the valve-controlled aperture 24. The diaphragm 16 and valves 28 for directing the exhaust gases are, it w1ll be noted, within the turbine casing, presenting a more compact arrangement than the more obvious one of having a by-- pass pipe arranged around the outside of the casing, connecting the inlet and exhaust pipes.

The arrangement thus far described, is designed for use with an engine in which the exhaust pipes are arranged between the rows of cylinders, that is to say, on the inside. With the Liberty motor, however, which has the exhaust pipes arranged on the outside, some modification is necessary and such modification is shown in Figs. 6 to 10.

Referring to Fig. 8, a diagrammatic representation of the arrangement of the exhaust pipes in the Liberty motor is shown, said exhaust pipes being indicated at 30. It is evident that it would be very awkward to lead the exhaust gases in the inlet cham ber 17 through ports in the base 9 in such a motor. In order to obviate this difliculty, the exhaust is led into the casing 7 through the inlet ports 31, in the side of the casing 7.

Adjacent'to the ports 31, the diaphragm 16 is bulged outwardly asat 32 to register with the farther side of the inlet port 31 as at the point 33. The rest of the diaphragm 16 is annular and conical in shape as in Fig. 1, the purpose of the bulge 32 being to lead the exhaust gases into the inlet chamber 17.

It will be noted in Fig. 2 that the inlet and exhaust pipes are located in substantially the same line. In Fig, 7, it should be noted, that while the inlet ports 31 are arranged in one line, the exhaust ports 34 corresponding to the exhaust ports 11 in Fig. 1, are arranged in a line at right angles to the line in which the inlet ports are arranged. This arrangement is necessary be: cause of the fact that both inlet and exhaust ports in the modified form shown in Figs. 6 and 7 are located in the side wall of the casing 7. The gases in Fig. 6 circulate 'as shown by the arrows, the gases entering through the ports 31, being guided by the bulge portion 32 into the inlet chamber 17, thence through the nozzles 20, buckets 2, into the exhaust chamber 18, thence out as shown by the dotted arrows in Fig. 6 and thence out throughthe ports 34 in a direction at right angles to the direction of entry.

Associated withthe casing are means for air cooling the turbine wheel 1, similar in principle and general arrangement to that disclosed in my co-pending application, Se rial No. 224,357, 'filed March 23, 1918.

Attached to the rim of the casing, there is an annular element 35, spaced slightly from the back plate 14 and extending from the rim of the casing inwardly, in substantially a radial direction and then it is bent upon itself as indicated at 36 in substantial parallelism with the side 37 of the wheel 1, thereby defining an air channel 38. Openings 39 may be cut in this element 35 for the escape of the air.

The centrifugal action of the wheel on the air in the passage 38 throws it outwardly toward the openings 39 and sucks in more cool air through the passage 38, thereby providing an effective and automaticcooling means for the wheel 1, which will cause more air to circulate, the faster the wheel goes. Associated with the element 39, there may be provided an air receiving horn to aid the ingress of the air as shown in the above-mentioned co-pending application, Serial No. 224,357, filed March On the other side of the wheel, a similar element 35 is provided, which surrounds the axis 3 and is spaced therefrom to provide an air passage 38'. Element 35' is bent around as at 36', to provide an air-passage 1 0 38', substantially parallel to the face 37' of the Wheel 1. The bottom of the casing 7 and element 35 are provided with suitable openings 39 for the escape of'the air. The passage of the cooling air will be obvious and is shown by the arrows. Element 35 is supported from the back wall of the easing at the point 40.

While I have shown and .described a specific embodiment of my invention, it should be understood that I do not intend that the invention be limited to the specific forms disclosed and that it should be understood the invention may be embodied in a number of different forms falling within the scope of the appended claims.

I claim I 1. A turbine easing comprising a main casing element provided with inlet and exhaust ports, a back plate attached thereto and adiaphragm associated with v said cas-v ing element and said back plate arranged to divide the easing into inlet and exhaust chambers.

2. The combination as claimed in claim 1, the three mentioned parts being stamped out of sheet metal.

3. A turbine easing comprising a main casing element provided with inletand exhaust ports, a back plate attached thereto and a diaphragm associated with said casing element and said back plate arranged to divide the easing intoinlet and exhaust chambers, the said diaphragm being substantially annular and attached to said main casing element toward its outer periphery.

1. A turbine casing comprising a main casing element-provided with inlet and exhaust ports, a back plate attached thereto and a diaphragm associated with said casing element and said back plate arrmged to divide the easing into inlet and exhaust chambers, the said diaphragm being substantially conical in section.

5. A turbine casing comprising a main casing element provided with inlet and exhaust ports, a back plate attached thereto and a diaphragm associated with said casing element and said back plate arranged to divide the easing into inlet and exhaust chambers, the said diaphragm being substantially conical in section and attached to the 'said main casingelement between the said inlet and exhaust ports.

6.,A turbine casing comprising a main casing element provided with inlet and exhaust ports, a back plate attached thereto, a diaphragm associated with said casing element and said back late arranged to divide the easing into; inlet and exhaust chambers and a nozzle element arranged at the inner part of said diaphragm.

7. A turbine casing comprising a main casing element provided with inlet and exhaust ports, a back plate attached thereto and an annular diaphragm attached at its periphery to said main casing element arranged to divide the easing into inlet and.

the main casing element, the back plate and the diaphragm being made of sheet metal;

10. The combination as claimed in claim 4, the main casing element, the back plate and the diaphragm being made of sheet metal.

11. The combination as claimed in claim 5, the main casing element, the back plate and the diaphragm being made of sheet metal.

12. The combination as claimed in claim 6, the main casing element, the back plate and the diaphragm being made of sheet metal.

13. The combination as claimed in claim 7, the main casing element, the back plate and the diaphragm being made of sheet metal. i

14. The combination as claimed in claim 8, the main casing element, the back plate and the diaphragm being made of sheet metal. 7

15. In combination with an internal combustion engine, a turbine adapted to be operated by the exhaust gases from said engine, a casing for said turbine, means within said casing to divide said easing into inlet and exhaust chambers, means to by-pass the gases from the inlet chamber to the exhaust chamber, and nozzle means associated with said dividing means.

16.In combination with an internal combustion engine, a turbine adapted to be 0perated by the exhaust gases from said engine, a casing for said turbine, means within said casing to divide said easing into inlet and exhaust chambers, adjustable means associated with said last-mentioned means to bypass the gases trom the inlet chamber to the exhaust chamber, and nozzle means associated with said dividing means.

17. In combination with a turbine, at casing, a diaphragm arranged within said casing to divide the easing into inlet and exhaust chambers and a series of nozzles positioned at the inner part of said diaphragm.

18. In combination with a turbine, a casing. a diaphragm arranged Within said casing arranged to divide the easing into inlet and exhaust chambers and a nozzle ring positioned at the inner partof said diaphragm.

19. In combination with a turbine, a casing, a diaphragm arranged within said casing arranged to divide the casing into inlet and exhaust chambers, a. nozzle rin pos1- tioned at the inner part of said diap ragm, and means to hold said diaphragm in engagement with said nozzle ring.

20. In combination with a turbine, a casing, a diaphragm arranged to divide the casing into inlet and exhaust chambers, a nozzle ring, said diaphragm being arranged to engage said nozzlering, means to attach said nozzle ring to the casing, said lastmentioned means, together with said casing and said diaphragm, defining the said inlet chamber.

21. A turbine casing, comprising a main casing element, made of but a single thick- 20 ness of metal, said main casing element being provided with inlet and exhaust ports,

a back plate attached to said main casing element, and a diaphragm associated with said casing element and said back plate, to 25 divide the casing into inlet and exhaust chambers.

Signed at Newark in'the county of Essex and State of New Jersey this 21st day of March A. D. 1918.

EARL H. SHERBONDY.

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