US2474404A - Combustion turbine - Google Patents

Description

June 28, 1949. I 5, c gso 2,474,404

COMBUSTION TURBINE Filed 060. 6, 1945 2 Sheets-Sheet 1 FIGA.

SA NFORD E R/cHES o/v INVENTOR ATTO R N EY June 28, 1949. s. E. RICHESON counusuou TURBINE 2 Sheets-Sheet mad Dec. e; 1945 SA NFOFD E R/CI/Es o/v INVENTOR ad f.

ATTO R N EY at which theya relatively high 3 Fig. 3 is the line 3-3 of Fig. 1;

- compressor.

' be provided with Patented June'28, 1949 I v 9 Claims.

My invention relates combustion turbines and has particular reference'to' turbines operated by hot gaseous products of combustion, the turbine operating a compressor for supplying air to a combustion chamber;

My invention has for its object to provide a (01. sou combustion turbine of the general character indicated above in which the compressor is so constructed as to reduce frictional losses to a point will practically disappear.

Another object of myinvention is to provide specially constructed blades which will withstand possible to maintain high operating temperatures in the turbine for increasing: its power output and efficiency. The useof high temperatures tercoolers inthe compressor, thereby also reducing losses and increasing efiiciency. Y

The foregoing and other objects and features and advantages of my invention are more fully explained in the accompanying specification and pose is delivered by a pump Mi operated by the drawing in which:

Fig. 1 is a'sectional bine;

Fig. 2 a detail sectional view of the blades;-

Fig. 4 is a sectional detail view oi the may turbine comprises a tubular My combustion i having gradually increasing casing or. stator elevational view of my turtemperature thereby making it makes it also possible to'eliminate the use .of in-' a; sectional view of the same taken on .vaporsi'rom the rotor chamber 18. F01: compressing the outside air, large vanes 30 are provided extending from the-outside of the front end plates it of the rotor and enclosed by'an inner portion ii of the casing 28; Vapors from the rotor chamber-l9 are exhausted through ducts 82 connected with a disc-shaped hollow impeller 33 having a narrow annular nozzle 34 opening into an annular Venturi restriction 35 opening into the casing 28. The impeller is provided with curved blades 36 as shown more clearly in Fig. 4, and stationary blades 31 are provided in-the Venturi 34, curved in the opposite direction, the blades of the impeller act as turbine blades for adding a rotary movement to the'shaft 8.

" higher operating temperature, the boiling point of mercury being .614 F. Mercury for this purpipe 48 into a cooling jacket 48 surrounding the stator. The vapors pass through the Jacket, being guided by spirally arranged baffles 48 which cause the. vapors to make several revolutions diameters from the rear or intake end (at the left also of a frusto-conical shape. The rotor is closed at the ends by end plates i1, i8 mounted on the shaft 8 and sealing the space 18' in the rotor.

Hot burning gases are supplied to the turbine blades from a combustor flsupported on a bracker 25 in communication with the intake opening of the turbine. Fuel, liquid or gaseous. is supplied to the combustor by a nozzle 26 which may.

operated by a conventional governor. Compressed air is delivered to the combustor by a pipe in Fig. 1) to the front'or exhaust end (at the tary blades l5 mounted on atubular rotor l8,

around the stator before theyemerge through a pipe 58. The outer shell of the stator is made of 'steel or other alloy which is not affected by mercury such as an alloy of lead, sodium, copper-and iron. The blades ll made of heat resisting alloy, 'and to facilitate the conduction of heat from the blades, 9. layer of a good heat conducting metal 5! is provided, such as silver, with silver'plugs 82 inside the blades ll (Fig. 2)..

The pipe 58 is connected to a nozzle 55 through which the mercury vapors are directed into the hollow shaft 6 through a Venturi restriction 8,8 for increasing their velocity and forming a seal for the vapors in the rotor'. The velocity is further" increased by causing the vapors to pass through radial tubes 51 extending to' the rotor,

' et 23 attached to the rear plate 2 and having an exhaust pipe 24 connected with an annular heata conventional throttle valve blades l5 which are made hollow inside to facili-' tate their cooling by the vapors. The rotor is also lined inside with a mercuryresisting metal or alloy,-with. a lining 58 of silver or other heat conducting material between the inner lining and the refractory metal of the blades (Fig. 2). The opening of the nozzle 68 is controlled by an inner nozzle rnovably supported in the rearof the enter nozzle 55 and'moved by a screw 6| controlled by a suitable conventional pressure responsive device 62 for maintaining a desired pressure at the nozzle. The inner nozzle 68 is connected by a pipe-68 with the pump 40 and delivers liquid mercury or other liquid into the nozzle 55. A thermocouple 53 is placed in the nozzle 55 and is connected with a, thermostat control valve 59 in the pipe 84 for regulating the temperature to regulate the flow of mercury. The liquid breaks up into droplets and boosts pressure and provides a frictionless seal, delivering a mixture of mercury vapors and liquid mercury into the hollow shaft 6 from which the mixture is projected by centrifugal force against the inner wall of. the rotor and the hollow spaces in the blades. 7

Presence of mercury vapors in the cooling medium makes it possible to maintain the turbine on a high efilciency level by raising the operating temperatures of the blades. vaporized in the coil 45 by the exhaust heat, is delivered at 700-800 F. into the spiral jacket 48 around the stator, cooling the stationary blades. The heated vapors are then injected into the hollow shaft 6 together with the mercury droplets, which are vaporized, reducing the temperature of the mixture to about 1000 F. A certain amount of the outside air is admitted through a clearance between a disc 65 on the nozzle 55 and a movable disc 66'slidably supported on the'shaft 6 and operated by a centrifugal governor 6'! which closes the clearance between the discs 65 and 66 .when the shaft is not rotating, thereby preventing loss of the vapors when the turbine is not operating. The amount of the air admitted through this clearance during rotation of the shaft can be regulated for maintaining a desired temperature of the vapors in the nozzle 55.

The vapors are elected. at a high speed from. the radial pipes propelled by the centrifugal force of the rotor which may make as much as 7000 R. P. M; Liquid mercury is evaporated by the heat of'the blades, and the superheatedl, vapors pass through the ducts 32 and are discharged at high velocity through the annular nozzle 34 into the collector 28 from which they are forced into pipes 10 connected with an annular condenser ll surrounding the stator. .The condenser is provided with a plurality of pockets 12 for the condensed mercury arranged at different points of the periphery so that the mercury can be collected in any position of the turbine as, for instance, when it is used on an airplane. The pockets are connected by pipes 13 with the intake of the pump 48. Valves 14 are provided in the pipes 13 operated by magnets .15 forclosing the valves when there is no mercury in'the pocket.

The mercury will be readily condensed since its temperature will be reduced to about 500 F.

Thus, the mercury,

tures, higher operating temperature can be reached even with the same materials as are now in use, and thus greatly increasing the overall efllciency.

Condensing temperature can be regulated by louvres 80 in an air Jacket 8| around the turbine. the louvres being operated'by a thermostatic control device 82 of a conventional type. The jacket 8 I has a common inner annular wall 83.

If water is used instead of mercury, then the condenser must be kept below 212 F. If desired, steam can be admitted into the combustion chamber, increasing the overall efllciency, but a.

' constant supply of water must be then available.

Such a system can be used.to advantage on locomotives, for instance.

The use of mercury in my system has an important advantage in that it eliminates the use of a cooling system for the compressed air, and greatly increases the efllciency of the turbine,

which depends on the temperature of the air be-.

fore expansion in the combustor. The elimination of the cooling system reduces the weight of the craft.

power plant thus rendering itpractical for air- The exhaust gases emerging through exhaust pipes, 85 can be directed to the rear of the aircraft, adding to the propelling power on the rocket principle.

Because of, the large massof the mercury vapors, their passage through tubes 51 increases the pressure virtually without friction'or loss of power in any substantial degree. The pressure is still further increased by the centrifugal compressor-nozzle 34, whose peripheral speed will be very great becauseof its large radius.-

'As an added means to prevent the loss of vapors, a closing'disc 86 is provided at the front sliding on,an extension 81 of the shaft 6 and held normally in a closing position against a flange 88 on the housing 3| by a spring 89 on the shaft 81 acting-0n centrifugal weights 80. The disc 86 s the blades 30 when the shaft 8 is rotating. Y

With such an arrangement it is possible to introduce liquid fuel into hollow rotor and to compress combustible vapors in the chamber 28 1 Itshould be noted that the intermediate lining by the air admitted through the large blades 30 and heated by the compression in the second stage, i. e., Venturi 35. The air, separated from the mercury, leaves the condenser II by pipes 16 connected with a heating coil 11 supported in the annular exhaust chamber 44 and are finally delivered by the pipe 21 into the combustor as was explained above.

The gases from the combustor pass into the turbine at a temperature of 1800-2000 F. or as high a temperature as the cooled blades and parts will stand. The ability to operate at such temperatures depends upon the materials alone, but by cooling the parts subjected to such temperadelivering these vapors directly to the combustor 22. v

A starting motor 9| is provided for the rotor operated from a battery (not shown) which will 7 be charged by the motor when it is operated as a generator during rotationof the turbine shaft.

.The' shaft 81 can be connected by suitable gears82, 88 with a shaft 84 of a propeller (not shown) or other mechanism.

58 between the shield metal and the refractory metal l4, 15 can be so selected as to take up the difference in expansion between the shield metal 7 and the refractory metal. a

It will .be understood that various features and principles of each of the embodiments of the. invention above described or referred to may be utilized or substituted in the other embodiments;

While the invention has been described in detall with respect to certain particular preferred examples, it will be understood by those skilled in the art after understanding the invention, that various changes and further modifications may be made without departing from the spirit and scope of the invention, and it is intended therefore in the appended claims to cover all such changes and modifications.

,pressor; means to set) rate the air from pors; and means to deliver the air into the comcompressors;

shaft rotatively supported in the end plates;-a' tubular rotor mounted on the shaft in the housseparated air by the exhaust gases; and means to 1deliver the heated air into the combustion cham- 4. In a combustion turbine the combination of a tubular housing; aplurality of rows of spaced stationary blades in the housing; a rear and a front end plate closing the ends of the housing;

a a shaft rotatively supported in the end plates; a

ing; a plurality of rows of blades on the rotor; the

rear end plate having an intake opening and the front end plate having an exhaust opening;-ave's-' sel in a communication withthe intake opening and comprising a combustion chamber; means to rear end plate having an intake opening and the admit a cooling medium into the rotor, the shaft being hollow at one end; tubular ducts extendingradially from the shaft to the rotor blades; means to admit airand a cooling liouid into the space- 4 in the rotor through the hollow. portion of the shaft; a compressor for he combustion chamber operatively connected to the shaft; means to admit-heated vapors with the air from the rotor into the compressor; means to admit heated va-- pors with the air from the vabustion chamber.

the rotor into the com- 2. In a combustion turbine the combination of a tubular housing; 'a-plurality of rows of spaced stationary blades in the housing; a rear and a front end plate closing the ends of the housing; a shaft rotatively supported inthe end plates: a tubular rotor mounted on theshaft. in the housing; a plurality of rows of blades'on the rotor; the rear end plate having an intake opening and the front end plate having an exhaust opening; a vessel in a communication with the intake opening and comprising a combustion chamber; means to admit a cooling medium into the rotor, the shaft being hollow at one end; tubular ducts extending radially from the shaft to the rotor blades, the rotor blades having cavitiesopening into the space in the rotor; the ducts being adapted to admit air into the rotor through the hollow portion of the shaft; a compressor'for the combustion chamber operatively connected with the shaft; means to admit heated vapors from the rotor into the and means to admit fresh air into the compressor for cooling and condensing the vapors; means to separate. the heated air from the condensed vapors; and means to deliver the heated air into the combustion chamber.

turbine the combination of 3. Ina combustion a tubular housing;'a plurality of rows of spaced Y stationary blades in the housing; a rear and a front end plate closin the ends of the housing; a

shaft rotatively-supported in the end plates; a tubular rotor mounted on the shaft in the housin a plurality of rows of blades on the rotor; the rear end plate having an intake opening and the front endplate having an exhaust opening; a vessel in a communication with the intakeopening and comprising a combustion chamber;

tubular rotor mounted on the shaft in the housing; a plurality of rows of blades on the rotor; the

front end plate having an exhaust opening; a vesand comprising a combustion chamber; means to admit a coolingmedium into the'rotor, the rotor blades having cavities opening into the space in the rotor; the ducts being adapted to admit air.

' operatively connected with the shaft; means to admit heated vapors from the rotor into the com: pressor; means to admit fresh air into the compressor'for cooling and condensing the vapors; means to. control the temperature of the condenser; means to separate the hot air in the condenser from the condensed liquid; and means to deliver the separated hot air into the combustion chamber.

5. In a combustion turbine the combination of a tubular housing; a plurality of rows of spaced stationary blades in the housing; a rear and a front end plate closing the ends of the housing; a shaft rotatively supported in the end plates; a tubular rotor mounted on the shaft in the housing; a plurality of rows of blades on the rotor; the rear end plate having an intake opening and the front end plate having an exhaust opening; a vessel in a communication with the intake opening and comprising acombustion chamber; means to admit a cooling medium into the rotor, the shaft being hollow at one end; tubular ducts extending radially from the shaft to the rotor blades; a Venturi restriction at one end of the shaft; a nozzle extending into the Venturi restriction; means to deliver a liquid through the nozzle and Verituri restriction into the hollow I shaft; and means .to admit outside air into the Venturi restriction. 1

6. In a combustion turbine the vcombination of a tubular housing; a plurality of rows of spaced vstationary blades in the housing; a rear and a front end plate closing the ends of the housing;

rotor; the rear end plate having an intake opening and-the front end plate having an exhaust opening; a vessel in, communication with the intake openingand comprising a combustion chamber; means to admit a cooling medium into the rotor; the shaft being hollow at one end; tubular ducts extending radially'from the shaft to the means to admit a cooling medium into the rotor, I

the shaft being hollow at one end; tubular ducts extending radially from the-shaft to'the rotor blades, the rotor blades havin cavities opening into the space in the rotor; the ducts being adapted to admit air into the rotor through thehollow portion of the shaft; a compressor for the combustion chamber operatively connected with the rotorblades; a Venturi'restrlction at one end of.

the shaft; a nozzle" extending into the Venturi restriction; means to deliver a liquid through the nozzle and Venturi restriction into the hollow shaft; means to admit heated vapors from the I rotor into the compressor; means to admit fresh air into the compressor for cooling and condensing the vapors; means to separate the heated air i from the condensed vapors; means to heat the shaft; means to admit'outside air into the Ven-' turl restriction; and means responsive to-the pressure in they nozzle to regulate the position of the nozzle in the Venturi restriction.

'h-In a'combustion turbine the combination of a tubular housing; a plurality of rows of spaced stationary blades in the housing; a rear and a front end plate closing the ends of the housing;

a shaft rotatively supported in the end plates;

sel in a communication with the intake opening I ing; a plurality of rows of blades on the rotor; the

rear end plate having an intake opening and the' front end plate havingan exhaust opening; a vessel in a communication with theintake opening and comprising a combustion chamber; means to admit a cooling medium into the rotor; the shaft being hollow at one end; tubular ducts extending radially from the shaft to therotor blades; a Venturi restriction at one end of the shaft; a nozzle extending into the Venturi renozzle and'Venturi restriction-into the hollow tion; and curved blades in the nozzle, the blades being curved in a direction for producing reaca tubular rotor mounted on the shaft in the housstationary blades in the housing;-

a shaft rotatively supported in the end plates;

front end plate closing the ends of the housing;

" a tubular rotor mounted'on the shaft in the housstrlctionrmeans to deliver a liquid through the shaft; means to admit outside air into the Venturi restriction; turbine'blades in the Venturi restric tion forces, augmenting the rotory torque of the rotor..

8. In a combustion turbine the combination of a tubular housing; a plurality of rows of spaced stationary blades in the housing; arear and a front end plate closing the ends of the housing; a shaft rotatively supported in the end plates; a tubular rotor mounted on the shaft in the housing; a plurality of rows of blades on the rotor; the rear end plate having an intake opening and the front end plate having an exhaust opening; a vessel in a communication with the intake opening and comprising a combustion chamber; means to admit a cooling medium into the rotor, the

shaft being hollow at one end; tubular ducts exinto the combustion chamber.

tending radially from the shaft to the rotor blades; means to admit a vaporizable liquid into the rotor through the shaft and through the ducts thereby obtaining vapors at a high pres-' mg; a plurality of rows ofblodes on the rotor; the rear'end plate having an intake opening and the thefront end'plate having an exhaust'opening; a vessel in a communication with the intake opening and comprising a combustion chamber; means to admit a cooling medium into the rotor, the shaft being hollow at one end; tubular ducts extending radially from thef-shaft to the rotor blades; means to admit a vaporizable liquid. fuel into the rotor. and thereby obtaining vapors at a high, pressure; 'a centrifugal compressor operated by the shaft; and means to admit the vapors SANFORD E. RICHESON. REFERENCES CITED The following references are of record in the file of this patent:

/ UNITED STATES PATENTS Number Name Date 1,164,091 Herz Dec. 14, 1915 1,421,087 Johnson June 27, 1922 1,828,782 Morton Oct. 27, 1931 2,154,481 Vorkauf Apr. 18, 1939 2,304,259 1 Karrer Dec. 8, 1942 and means to admit the vapors into the" a rear and a

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