US1310675A

US1310675A - sherbondy

Info

Publication number: US1310675A
Authority: US
Publication date: 1919-07-22
Anticipated expiration: 1936-07-22

Description

E. H. SHERBONDY.

NOZZLE RING. APPLICATION FILED APR. 8. I9I8..

Patented July 22, 1919.

2 SHEETSSHEET lv v w l/VVE/VTOR Ear-Z f2. Sherbonda Z QM/WI ATTORNEY ms COLUMBIA PLANOGRAPH cm, WASHINGTON, D. C.

E. H. SHERBONDY. NOZZLE RING. APPLICATION FILED APR. 8. 191a.

Patented July 22, 1919.

2 SHEETS-SHEET 2- IIVVE/VTOR Ea T-Z .li. flher'bond/a Br 6 ATTORNEY EARL H. SHERBON'DY,OECI1EVELANDK, OHIO.

NOZZLE-RING.

Specification of Letters Patent.

Patented July 22, 1919.

Application filed April 8, 1918. Serial No. 227,331.

This invention relates to a nozzle ring for a turbine and to a method of making same. It is an object of the invention to provide a one piece nozzle ring, having a body portion which serves as means for mounting the ring as a whole. The nozzle ring in question, is intended and adapted to be used in connection with a gas operated turbine of a type shown in my co-pending case, Serial No. 224.892, filed March 26, 1918.

Other objects and advantages will appear as the description proceeds.

Referring now to the drawings, in which similar reference characters indicate similar parts, Figure 1 is a side view partly in section, showing the nozzle ringin position 1n a turbine casing; Fig. 2 is a side view of the blank at one of the stages of manufacture, Fig. 3 is a sectional 'view on an enlarged scale of the same; Fig. 4: is development of the edge of the nozzle ring after the slots have been cut; Fig. 5 is a view on line 5-5 of Fig. 4 Fig. 6 is a view similar to Fig. 1 at a later stage of manufacture; Fig. soft alloy, profiling; Fig. 9 is a front view of the finished nozzle ring and Fig. 10 is a view, partly in section and partly in per'spective ofthe same. i

The first stage of the operation of making the one piece nozzle ring, is to take a thickwalled metal tube of a material which will withstand the high temperatures met with in a gas operated turbine.

The length ofthis tube may be substantially equal to the line A,B, Fig. 3, and the thickness of said tube may be substantially equal to line A D, Fig. 3. The excess metal is then cut away, leaving a comparatively thickend portion 1, the annular portion 2 and an upturned-portion 3; It should be mentioned in this connection, that Fig. 3

shows a section through an upper wall of the tube.

The end portion 1 is now undercut as at 1 all the way around, so thata PONY/1011 w1ll overhang this 1 out.

I shows the nozzle ring filled witha Fig. 8 shows the nozzle ring after 1 The next stage in making the nozzle ring is to out the slots in the portion 1. These slots designated S, are milled in the edge of the end portion 1 in such a manner that the slots S are helical with respect to a longitudinal axis'ofthe original tube, that is to say, the longitudinal axis of the annular portion 2. The cutting of these slots leaves the blades 5 outstanding from the base of the portion 1, it being evident that the blades 5 will also be helical with respect to the axis of the annular portion 2.

During the said milling operation, the work is fed longitudinally, that is, in a direction parallel to the axis of the portion 2, a distance A F, equal to the width of the portion 1. At the same time, the work isrotated about the axis of the annular portion 2 an amount equal to the distance G H, 'Fig. 4; the milling cutter during both of these motions, while itself rotating, does not move otherwise. The resultant of these two motions causes a helical slot to be out, which in the development in Fig. 4:, ap pears as a diagonal slot. It should be understood, however, that the body of each slot S, is everywhere equidistant from the axis of the portion 2, that is to say, it winds helically around saidaxis.

It will now be apparent that portions 5 of the blades 5, to the right of the line 4 4', representing the inner edge of the undercut portion 4, will overhang said undercut portion, as shown in Fig. 5. The-next stage in the making of the nozzle ring is to bend these overhanging portions 5 toward the axis of the portion 2, as shown in Fig. 6. The gases are intended to pass through the nozzle ring in a direction shown by the arrows in Fig. 6. The purpose of the justmentioned bending, is to change the direction of the opening of the slots S, so that the gases that are going to operate the turbine will be more readily taken into the slots S.

This bending operation can be carried out in any desired manner and as a matter of practice, it is accomplished by first heating the portions 5 in an oxyacetylene flame to a sufliciently high temperature, then bending them as shown in a suitable jig. Only the parts 5 of the blades 5, overhanging the undercut portion 4, are bent, the purpose of the slot 4 being to permit this bending.

The nozzle ring is intended to be located in turbine casing 6, as shown in F ig. 1 and the outer edge of the nozzle ring must be shaped to provide a proper gas tight seat for the diaphragm 7, located in the casing 6. The casing 6 carries inlet and exhaust pipes 8 and 9, and the diaphragm 7 is within the casing 6, between these two pipes. The annular portion 2 of the nozzle ring, the diaphragm 7 and the bottom of the casing 6, together define an inlet chamber 10.

In order to properly profile the blades 5 plete. Holes may be drilled in the por tion 3 to serve in mounting the whole in the casing 6.

It will thus b seen that I have provided a one piece nozzle ring which carries integral therewith, means for supporting it directly on the turbine casing, and which itself serves as a means for seating a diaphragm.

In a structure of this kind, where unusually high temperatures are met with, it will be evident that it is of distinct advantage to have the blades integral with the body of the ring, because in such a structure, there is no opportunity for erosion, due to the high velocity, hot, exhaust gases causing a weakening of separate connections between the nozzle blades and nozzle ring. The portion 2 may be chamfered at the point 18 for clearance purposes.

It should also be noted that the portion 2, serves as a mounting for the nozzle ring and also aids in defining the inlet chamber 10. It should also be noted that the cross-sectional area of the slots S gradually decreases from right to left of the drawing. This type of nozzle presents known advantages in turbine nozzle design.

WVhile I have shown one method of making this nozzle ring, it should be understood that this method may be modified and that the nozzle ring itself may be modified as defined within the scope of the appended claims.

I claim- .1. The method of making a turbine nozzle ring, comprising cutting away a thick-walled tube to leave an end portion of substantially the thickness of the original tube, and cutting slots in said end portion helical with respect to the axis of said tube.

The method of making a turbine nozzle ring, comprising cutting away a thickwalled tube to leave an end portion of substantial thickness and a relatively thin annular portion, undercutting said end portion, and cuttitng slots in said end portion helical with respect to the axis of said tube.

3. The method of making a turbine nozzle ring, comprising cutting away a thick-walled tube'to leave an end portion of substantial thickness and a relatively thin annular portion, undercutting said end portion, and cutting slots in said end portion helical with respectto the axis of said tube, then bending the blades between the slots and adjacent the undercut portion toward the axis of said tube.

4. The method of making a turbine nozzle ring, comprising cutting away a thick-walled tube to leave an end portion of substantial thickness and a relatively thin annular portion, undercutting said end portion and cutting slots in said end portion helical with respect to the axis of said tube, then bending the blades between the slots and adj acentthe undercut portion toward the axis of said tube, then filling said slots with an alloy and turning the outer part of said blades down to a profile. 1

5. The method of making a turbine nozzle ring, comprising cutting helical slots in the periphery of a solid annular blank, said slots being helical with respect to the axis of said ring along the edge of said blank.

6. The method of making a turbine nozzle ring, comprising undercutting a solid annular blank and cutting helical slots in the periphery of said blank, said slots being helical with respect to the axis of said ring.

7. Themethod of making a turbine nozzle ring, comprisingundercutting a solid annular blank, cutting helical slots in the periphery of said blank, said slots being'helical with respect to the axis of saidring, then bending toward said axis that part of the walls of the slotsthat overhang said undercut portion. I I

8; The method of making a turbine nozzle ring, comprising undercutting a solid annular blank, cutting helical slots in the periphery of said blank, said slots being helical with respect'to the axis of said ring, then bending toward said axis that part of the walls of the slots that overhang said under cut portion, then filling the'said slots with an alloy and turning down the side of the 1iilng opposite the undercut portion to a prowith said annular portion, said blades gradually decreasing in height from one part to the other, and'a diaphragm seated on this last-mentioned part.

10. A turbine nozzle ring, comprising an annular portion and nozzle blades, helical with respect to the axis of said portion, said 9. A turbine nozzle ring, comprising an. annular portlon and nozzle blades integral blades gradually decreasing in height from one part to the other, and a diaphragm seated on this last-mentioned part.

11. A turbine nozzle ring, comprising an annular portion and nozzle blades, helical with respect to the axis of said portion and integral therewith, said blades gradually decreasing in height from one part to the other, and a diaphragm seated on this lastmentioned part.

12. A turbine nozzle ring, comprising an annular portion, blades defining nozzles on one part of said ring, said annular portion serving as supportin means for supporting the nozzle ring, said blades gradually decreasing in height from one part to the other, and a diaphragm seated on this last mentioned part.

13. The combination as claimed in claim 12, the mentioned parts being made integral.

1%. A turbine nozzle ring, comprising an annular portion, blades integral therewith defining slots helical with respect to the axis of said annular portion, located toward one end of the annular portion, the other end of said annular portion being adapted to be supported on the turbine casing.

15. A turbine nozzle ring, comprising an annular portion, nozzle blades defining slots helical with respect to the axis of saidannular portion, said nozzle blades being undercut at one side.

16. A turbine nozzle ring, comprising an annular portion, nozzle blades defining slots helical with respect to the axis of said annular portion, said nozzle blades being undercut at one side, said blades, adjacent said undercut portion, being curved toward the said axis,

17. The combination as claimed in claim 15, the mentioned parts being integral with one another.

18. The combination as claimed in claim 16, the mentioned parts being integral with one another.

19. A turbine nozzle ring, comprising an annular portion, blades defining slots helical with respect to the axis of said annular portion, the said blades each decreasing gradually in height from one part to the other, whereby the slots are caused to decrease in cross-sectional area from one part to another.

20. In combination with a turbine, a casing, a diaphragm arranged to divide the casing into inlet and exhaust chambers, a nozzle ring cut away at its outer edge and means to hold said diaphragm in engagement with the cut away portion of said nozzle ring.

21. 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 with said nozzle ring and means to attach said nozzle ring to the casing.

In testlmony whereof I aflix my signature.

EARL H. SHERBONDY.

Copies of this patent may be obtained for five cents each, by addressing the Commissioner of Patents, Washington, D. 0.