US2333053A

US2333053A - High temperature elastic fluid turbine

Info

Publication number: US2333053A
Application number: US364572A
Authority: US
Inventors: Stroehlen Richard
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 1940-01-05
Filing date: 1940-11-06
Publication date: 1943-10-26
Anticipated expiration: 1960-10-26

Description

R. STROEHLEN 2,333,053

HIGH TEMPERATURE ELASTIC FLUID TURBINE oct. 26, 1943.

Filed NOV. 6, 1940 Inventor:

His Attovney.

Qcharci Street-lien,

Patented 011.26,

, unirse STAT-Es PATENT 'orrlca mama sti-nemen, Gew-n mais New York Application November i n In Germany BerlinLGermanLassignor'to mm, a corporation of s, 1940, sex-n1 No. 364,572 January 5, 1940 2 Claims. (Cl. 60-41) The present invention relates to high temperacooling the nrst 4stage bucket wheel and other elements subjectto the high temperature of the operating fluid conducted to the turbine.` The invention is of special signincance in connection with gas turbines operated with exhaust gases from internal combustion engines at temperatures of 600 C. and above, although it is vnot limited thereto.

For a consideration of what I believe to be novel and my invention, attention is directed to the following description and .the claims appendecl thereto in connection withthe accompanying drawing. y

In the drawing 1` illustrates a sectional view of a gas turbine embodying my invention; and Fig. 2 illustrates a modification of a part of Fig. l.

The invention comprises a-rotor Il with a i shaft II supported on a bearing I2. The rotor has a plurality of spaced rows of buckets I3 and is enclosed within a casing I4. High temperature gas is conducted to the rotor by means of an inlet chest or nozzle box I5 forming an annular row of nozzle partitions .I6 for conducting gases from the nozzle boxv to the first row of bucket wheels. vThe gases discharged from the ilrst row of buckets or from the rst-stage bucket wheel are conducted to a second row of buckets by a vdiaphragm or nozzle partition I1 supported on the casing. Similar 'diaphragms are associated with the succeeding rows of buckets. v In accordance with my invention the l nozzle partitions 'I6' are `formed with radial bores or openings I8 anda cooling ring I9 located in an opening formed by the casing is connected to the" rounded by a'casing 23 supported on the inlet v of air or like cooling medium through the chanchest Il vvand surrounding the turbine casing I4 to denne channel 24. This channel'is open at its right-hand end to atmosphere. Rows of

guide blades

25 and 23 are arranged on opposite sides of the cooling blades or vanes 22.

' During operation the blades 22 force a stream nel 24. The cooling air is conducted through the radial openings I3 of the first stage nozzle blades I6 and discharged therefromthrough a cylindrical channel -21 surrounding the bearing I2. The cooling air or like medium forced through the cooling channel 24 effects cooling of the blades 22 and the-cooling ring I9 and also of the first stage nozzle blades or partitions I 6.

. The cooling air in the channel 21 reduces the I with a casing. The rim of the ring 3l is formed transfer of heat from the nozzle box to the bearing and the rotor. leakage ofgases'from the first stage along the shaft'is reduced by the provision of packings 28 and 29 sealing the shaft II to the channel 21. A

In place of gaseous cooling medium liquid may be used for cooling the cooling ring. This is especially possible in arrangements which do not requirer cooling of the nozzle or diaphragm partitions. Such an arrangement is shown in Fig. 2 in which outer ends of bucket blades 30 are connected to a cooling ring 3| corresponding to the ring I9 of Fig. l. The sides of the cooling ring .are provided with annular grooves 32 to define part of a labyrinth sealing arrangement with a plurality of radial ribs or cooling vanes 4als 33, in the present example projecting into a conthe radial width of the ring I9 in the present instance is about equal to the radiallength of the buckets. The ring I9 is sealed on opposite sides yto the turbine casing by means of known type of labyrinth packings 20 and 2l. With this arrangement a considerable amount of heat absorbed by the first row of buckets is dissipated may be supported on or form part'of the turbine casing. .Inv some instances the container 34 with cooling liquid may be omitted, in which case the ribs 33 and the cooling ring are cooled solely by the air coming in contact therewith.

Having described the method of operation of my invention, together' with the apparatus which I now consider to represent the best embodiment thereof, I desire to have it understood that the apparatus shown is only illustrative andv that the invention may be carried out by otherv with a cooling ring secured to the outer ends of the buckets, a labyrinth type packing between the cooling ring and the nozzle box, a cooling channel enclosing the ring and connected to the hollow partitions, and impeller blades secured to the outer end of the ring for forcing cooling medium through the channel and the hollow par titions.

2. An elastic fluid turbine comprising a. casing forming anozzle box with a rowvof hollow nozzle partitions, a rotor with a shaft having a rst stage bucket wheel for receiving elastic fluid from the nozzle box, saidbucket wheel having a row of radially arranged buckets with a cooling ring secured to the outer ends ci the buckets, a labyrinth type packing between the cooling ring and the nozzle box, a cooling channel enclosing the ring and connected to the outer ends of the hollow partitions, impeller blades secured to the outerend of the ring for forcing cooling medium through the channel andthe hollow partitions, and another cooling channel surrounding the shaft and connected to receive cooling medium from the inner ends of the hollow partitions to reduce heat trensfer from the nozzle box to the rotor.

RICHARD STROEHLEN.