US2603063A

US2603063A - Combustion turbine system

Info

Publication number: US2603063A
Application number: US162901A
Authority: US
Inventors: James L Ray
Original assignee: Allis Chalmers Corp
Current assignee: Allis Chalmers Corp
Priority date: 1950-05-19
Filing date: 1950-05-19
Publication date: 1952-07-15
Anticipated expiration: 1969-07-15

Description

July 15, 1952 J. L. RAY

COMBUSTION TURBINE SYSTEM Original Filed Oct. 28, 1943 Patented July 15, 1952 2,603,063 COMBUSTION TURBINE SYSTEM James L. Ray, Long Beach, Calii., assignor to Allis-Chalmers Manufacturing Company, Milwaukee, Wis.

Continuation of application Serial No. 507,969, October 28, 1943. This application May 19,

1950, Serial No. 162,901

Claims.

This invention, originally disclosed in copending application Serial No. 507,969, filed October 28, 1943; now abandoned, of which the present application is a continuation, relates to the control and regulation of continuous combustion gas turbine systems embodying separate compressor driving and excess power developing turbine receiving motive fluid from one or more combustion chambers in which the pressure of the motive fluid is subject to change in response to variations in the quantity of motive fluid entering the power turbine and has for its primary object the maintenance of a high degree of overall system efliciency as the load output of the power turbine varies.

More particularly, the invention resides in varying the flow capacity and the power output of the compressor turbine as the quantity of fluid entering the power turbine changes in order to compress and deliver to the combustion chamber a quantity of air commensurate with the power requirements of both turbines. In other words, the flow capacity and the power output of the compressor turbine are varied as the load on the power turbine changes in order to develop and apportion to said turbines motive fluid commensurate in quantity and energy content with their respective load requirements.

Accordingly, the invention consists of the variou procedures, correlations of features and arrangements of parts as is more fully set forth in the appended claims and in the detailed description, in which:

Fig. 1 schematically illustrates a continuous combustion turbine system embodying the invention; and

Fig. 2 illustrates a modifying connection between the power turbine governor and the pressure and temperature responsive devices.

Referring to the drawing, it is seen that a continuous combustion gas turbine system embodying the invention may include a combustion gas generating means or combustion chamber I provided with a fluid fuel burner 2 to which fuel is supplied from a suitable source (not shown) through a pipe 3 in which is disposed a regulating valve 4, a compressor 6 delivering air to the burner and of combustion chamber I through a conduit I, a multistage turbine 8 drivingly connected with the compressor 6 and having a first or high and one or more intermediate pressure stage inlet portions 9, II and I2 connected with the opposite or discharge end of combustion chamber I by means of conduits I 3; I8 and I4, respectively, valves I1 and I8 controlling the flow of gas through conduits I4 and I6, respectively,

and an excess power developing turbine I9 drivbine I9 have'reciprocable

elements

28 and 29, re-

spectively, interconnected for jointly and severally actuating the regulating valve 4 by means of a floating lever 3I having one end connected with element 28, a lever 32 which is fulcrumed intermediate its ends at 33 and has one connected with element 29, a link 34 interconnecting the adjacent ends of levers 3I and 32, a link" 36 connecting an intermediate portion of lever 3I with one end or a floating lever 31, a link 38 connecting an intermediate portion of lever 3! with one arm of a bell crank lever 39 and a link 4I connecting the other arm of hell crank lever 39 with the valve 4. The opposite end of floating lever 31 is connected by means of a link 42 with an intermediate portion of afloating lever 43 which has its opposite ends connected with temperature and pressure regulating or limiting devices 44 and 46, respectively, for movement jointly and severally as the temperature and/or pressure of the gas within the combustion chamber varies or exceeds predetermined limits. The throttle valve 24 in conduit 23 is operatively connected with the element 29 of governor 21 for movement therewith .by means of a bell crank lever 41 and a link 48.

The hereinbefore described interconnection of governors 26 and 21 is such that when the system is in operation, an increase in the speed of compressor turbine 8 (in any system embodying the invention, the speed of the compressor is always the same or proportional to that of the turbine driving same) results in an upward movement of element 28, a clockwise movement of floating lever 3I about its point of pivotal connection with link 34, an upward movement of link 36, a clockwise movement of floating lever31 aboutits point of pivotal connection with link 42, an upward movement of link 38, a clockwise movementof bell crank lever 39, a movement of link 4I toward the left, and a closing movement of valve 4. Obviously, if the speed of the compressor turbine decreases, the element 28 of governor 26 moves downward and effects an opening movement of the valve 4. However, if the speed of the power turbine I9 increases, the element 29 of governor 21 moves closing movement of the valve 4. Obviously, a'decrease in the speed of power turbine. i9 will move element 29 of governor 2'! in the oppcs'ite-dh'ec,

tion and effect an opening movement of botvalves, that is, the valves designated 4 and 24.

to its fully open position, that a further upward movement of piston 5| moves valve 11 from its fully closed to its fully open position, and that the opening of valves I8 and/or I! as just described reduces the number and/or effectiveness of ,the active or. power producing stages in the tuEbine BQWhich. materially decreases the resistance to the flow of gas therethrough and thereby greatly increases its flow capacity.

The valves l1 and E8 in conduits. l4 and .lfi are arranged to be sequentially opened and closedby a servomotor 49 having a piston 5| provided with oppositely extending stem or rod portions. 52 and 53 of which rod portioniBi-i is connected with an intermediate portion of a lever element 54 having. its opposite ends connected with the valves Hand l8 by means of links 56 and.5'l, respectively; and of which rod portion 52 is-connected with one endof' a lever 58 which is fulcrumed intermediate its end at 5-9.andhas its other end connected with an intermediate portion o f;a floating lever 6| by means of a link 62. Oneend of lever 6|. is connected by a link 63 to a portion ofg'lever 32 intermediate its fulcrum 33- and its pointjof connection. with governor e1ement29, and the other end of lever fil is connected with the stem ot a balanced pilot valve Mwhich controls the.- connection. between the fluid supply pipe 66 and, the pipes 61 and 6S and between the pipes 61 and 68- andthe drain or return pipes 69 and] l, respectively; the construction beingsuch that whenthe valve 64 is in its neutral or shown position no fluid flows-into or out-of servomotor49, that when. the valve 64 is moved downward from the:- positionshown, fluid under pressure ispadmittedto the upper side of piston 5|. through pipe 61 and the fluid beneath the piston is free to flow therefrom through pipes 68 and II, that when the valve is moved upward from the posiof the element and a fixed support 13- and up-' ward1 movementof the right hand end of element 54- aided by a tension spring- (-5 and is limitedby an adjustable stop; 14. Consequently, as the servomotor piston 5| moves upward from its shown position, lever element 54 moves in .a counterclock-wise direction about its point of pivotalconnection with link 56 and until the right hand end thereof engages stop-l4 atter which a further upward movement of piston 5| results in lever element 54-moving in a clockwise direction aboutitspoint of pivotal connection withlink 51 andluntil the. spring l2l isfully compressed; further upward movement of theservomotor piston and damage tothe parts normally actuated by the rod portion 53 thereof beingpermitted and prevented, respectively, .by the resiliently interconnected parts I6 of rod portion.5.3..

, It should now. be obvious that an upward movement of servomotor piston 5! from. its shown positionfirstmoves valve 18 from. its fully closed The movement of pilot valve 64 away from its neutral position is effected by the governor 21 of power turbine 13; the arrangement being such that when. the speed of the power turbine increases, itbeing; assumed that the various parts are shown as positioned to obtain a maximum powerzoutput fromboth turbines, the element 29 of; governor, zlwill. move downward and simultaneously'effect (a) a closing movement of throttle valve 2.4, (b) a closing movement of fuel valve 4, and (c) an upward movement of pilot valve 64 which in turn operates servomotor 49 to move valve I8 toward'its fully open position. A partial closing of throttle valve 24 tends to increase the pressure of the-motivefluid within combustion chamber I and as a result. the speed of the compressor may increase sufliciently to deliver more air to the combustion chamber and to render governor 25 operable to effect a further closing movement of fuel valve 4. However, although the delivery of more air to the combustion chamber does tend to further increase the pressure of the motive fluid, the closing movement of. fuel valve 4 reducesthe heatinput and thereby the temperature and to some extent the pressure of the motive fluid while a partial opening of valve l8 also. operates. to reduce the pressure of the motive fluid by decreasing the resistance to the, flow of motive fluid through the turbine 8 which in turnincreases its flowcapacity with. a corresponding decrease in the power developed thereby. I

Obviously, with the parts positioned as previously assumed, the. extent to which the throttle and fuel regulating; valves 24 and'4, respectively, are closed and. the extent to which the-valves I8 and/or H are opened depends entirely upon how much load is removed from the power turbine I9. If, for example, the load on the power turbine drops to zero, the throttle valve 24 will be nearly or fully closed,v the fuel regulating valve 4 will remain open. suificiently to meet the. heat input power requirements of thecompressor turbine, and the valves [8 and I! will. be fully open. If when the valves are positioned as just described, the load on: the power. turbine increases, the speed will commence to decrease and the element 29 of governor 21 will move upward effecting a counterclockwise movement of lever 32 and a consequent opening movement of fuel valve 4 and a downward movement of. pilot valve 64; the latter admitting fluid under pressure to the top side of piston 5| which moves downward and effects a counterclockwise movement of lever element 54 about: its point of pivotal connection with link 51 and thereby a closing movement of valve IT. The primary'function of tension spring 15 being to hold the right handend of lever element 54 against stop 14- until the valve I1 is fully closed whereupon a further downward movement of piston 5! causes lever element 54 to pivot clock wise about its-point of connection with link 56 and movev valve I8 toward its fully closed position against the action of spring 15.

As previously indicated, a. closing movement oi throttle valve 24 increases the resistance. to the flow of motive fluid through the conduit 23 and thereby tends to increase the pressure of the motive fluid within the combustion chamber while the opening of valves l1 and I8 reduces the resistance to the flow of motive fluid through the turbine 8 and thereby tends to decrease the pressure of the motive fluid; the opening and closing movement of the valves l1, l8 and'24 being preferably" so correlated in the illustrated system that the pressure of the motive fluid within the combustion chamber increases and decreases as the load on the power turbine increases and decreases, respectively. 'In this connection, the power developed by compressor turbine 8 is proportional to the drop in pressure and temperature of the gases passing therethrough and by properly selecting the number and location of the inlets to the intermediate pressure stages of the compressor turbine and by properly correlating the admission of motive fluid to said inlets with the admission of motive fluid to the power turbine, the power developed by the compressor turbine and thereby the quantity of air delivered to the combustion chamber can be read-v ily varied in accordance with the power requirements of the system for all conditions of load while maintaining the air near the maximum permissible operating temperature in order to obtain high 'efliciency. The number and the location of the inlets to the intermediate stages of the compressor turbine and the particular manner in which the admission of 'motive'fiu'id to said inlets is correlated with the admission of motive fluid to the power turbine is of course dependent upon the operating characteristics of the turbines and compressor which can-be readily determined by any one skilled in the art and having once determined said characteristics and the nature of load to be carried by the system upon whether the best efliciency for a changing load is obtained by varying the quantity and the temperature and/or pressure of the motive fluid or by merely varying the quantity of motive fluid while maintaining its temperature and pressure at the optimum values.

In the disclosed embodiment of the invention, the turbine and compressor characteristics and the nature of load may be assumed to be such that maximum thermal efliciency is obtained'by maintaining the temperature of the motive fluid substantially constant at a predetermined value throughout the entire load range. Consequently, the position of the fuel regulating valve 4 and thereby the heat input to the system is controlled jointly and severally by governors 26 and 21 in I order to maintain the temperature of the motive fluid substantially constant as the load on the power turbine varies and the positions of valves [1, l8 and 24 are controlled by governor 21 in order to vary and apportion the quantity of motive fluid flowing through the turbines in accordance with their respective load requirements while maintaining the pressure of the motive fluid within the combustion chamber at an optimum value; the function of the temperature and pressure responsive devices 44 and 46 being in this case to terminate operation of the system whenever the temperature and/ or pressure of the motive fluid exceeds predetermined maximum limits. However, if the operating characteristics of the turbines and compressor and nature of the load to be carried by the system are such as to necessitate varying the quantity and the temperature and/or pressure of the motive fluid in order to obtain the best overall efliciency, this can be readily done with the illustrated apparal8 and 24 are opened and: closed in response't a predetermined degree of load change. i The invention is applicable to all types of combustion turbine systems embodying separate compressor driving and excess power developing turbines and although the'invention' has been shown and disclosed in connection with a system embodying only one combustion chamber and only one compressor driving and one excess power developing turbine, it should be understood that it is not desired to limit the invention torvthe exact details of construction and modes of operation herein shown and described, as various modifications within the scope of the claims may occur to persons skilled in the art.

It is ,claimedand desired to secure by Letters Patent:

1. A gas turbine system, comprising: a' 'combustion gas generating means having a fuel inlet; a compressor delivering air to said generating means; a turbine drivingly connected with said compressor; an excess power developing turbine; said com-pressor'turbine and said power turbine having separately rotatable drivingv shafts; means severally connecting an inlet to'said compressor turbine and an inlet to said power turbine with said generating means; means responsive'to change in load on said power turbine; means responsive directly and solely to said load responsive means for varying the flow of gas to said power turbine; and means responsive to said load responsive" means'for varying the flow through said fuel inlet;

2'. A gas turbine system, comprising: a combustion gas generating means having a fuel inlet; a compressor delivering air to said generating' means; a turbine drivingly connected with said compressor; an'excess power developing turbine; said compressor turbine and said power turbine having separately rotatable driving shafts; means severally connecting an 'inlet to said compressor turbine and an inlet to said power' turbine 'with said generating, means; means responsive to change in load on said power turbine; valve means for controlling the flow of gas to'said power turbine in response tosaid load change responsive means to increaseand decrease said flow in the same sense as change in load; valve means for controlling the flow of fuel through said fuel inlet in response to said load change responsive means to increase and decrease said fuel flow in the same sense as change in load; second load responsive means responsive to changes in load on said compressor turbine; and means responsive to said second load responsive means for controlling said fuel valve means to increase and decrease the fuel flow in .the same sense as change in load on, said compressor turbine. a a h 3. A. gasturbine system, comprising: a combustion gas generating means having a fuel inlet; a compressor delivering air to said generating means; a turbine drivingly connected with said compressor; an excess power developing turbine; said-compressor turbine andsaid power turbine ;hay ing separately rotatablezrdrivingt aces-pea shafts; means severally connecting, an inlet to said compressor turbine. and; an: inlet .to: said power turbine with said generating means; means responsivetochange inload on said power turbine; means responsive to. said load responsive means-for varying theflow of gas to said power turbine; second. load responsive meansresponsive to-the loadro'n saidcompressor turbine; and means responsive to said second load responsive means; for varying; the flow through said fuel inlet; f 7

4. A gas" turbine system; comprising: i a combustion: gas generating means having a fuel inlet; a compressor delivering air to said generating means; a turbine drivingly connected with said compressor; an excess power developing turbine; saidcompressor turbine and said power turbine having separately rotatable driving shafts; means severally connecting an inlet to said compressor turbine and an inlet to said power turbine with said generating means;

means responsive'to changein load on saidpower' turbine; means responsive directly and solely tosaid load responsive means-for varying the flow of gas to said power turbine; means-responsive to said load responsive means for varying the flow through said fuel inlet; second load re sponsive meansresponsive to changes in load on said compressor turbine; and means responsive-to said second load responsive means for varying the flow throughsaid fuel inlet.

5.A- gas turbine system, comprising: a combustion gas generating means having a fuel inlet; a compressordelivering air to said generating means; a multistage turbine drivingly connected with saidcompressor and having separate inlets for the first and one or more intermediate stages thereof; an exeesspower developing turbine; said compressor turbine and said power turbine having separately rotatable driving shafts respectively; means severally connecting said separate inlets for theiirst and one or more intermediate stages of said compressor turbine and the inlet to said power turbine directly with said generating means, and means responsive to change in load on said power turbine for controlling the direct flow of gas to an intermediate stage of said compressor turbine.

6. A gas turbine system, comprising: a combustion-gas generating means having a fuel inlet; a compressor delivering air to said generating. means; a multistage turbine drivingly connectedwithsaidcompressor and having separate inlets'for the first and one or more intermediate stages thereof; an excess power developing turhim; said compressor turbine and said power turbine having separately rotatable driving shafts respectively; means severally connecting said'separate inlets for the first and one or more intermediate stages ofsaid compressor turbine and the inlet to said power turbine with said generating means, and means responsive to change in load on said power turbine for controlling the direct flow of gas to an intermediate stage of said compressor turbine; second load responsive means responsive to change in load on said compressor turbine; and means responsive to said second load responsive means for varying the flow through said fuel inlet.

7. A gas turbine system, comprising: a combustion gas generating means; a compressor delivering air to said generating means; a multi-- stage turbine drivingly connected with said com pressor and having separate inlets for the first and one or more intermediate stages thereof; an excess power developing turbine; said com pressor turbine andsaid power turbine. having separately rotatable'driving shafts respectively; means severally connecting said separate inlets for the first and oneor more intermediate stages of said compressor turbine and. the inlet to said power turbine; directly with 'said' generating means;-means-,responsive to change in load on said power turbine; .valve means responsive to.

said load responsive-means interposed between said inletjto said power turbine and said generating means forcontrolling the flow of gas to said power turbine; and valvemeans responsive.

to said load responsive means interposed between an-intermediate stage of said compressor turbine and said generating'means for controlling the direct flow of gas from said generating means to said' intermediate stage.

8. A gas turbine system, comprising: a combustion gas generating means; a compressor delivering air to saidgenerating means; a multi-- stage'turbine drivingly connected with said compressor and having separate inlets for the first and one or more intermediate stages thereof;

an-excess power developing turbine; said com pressor turbine and-said power turbine having separately rotatable driving shafts respectively; means severally connecting said separate inlets for the'first and oneor more'intermediate stages of said compressorturbine and the inlet to said power turbine directly with said generating.

means;'- means responsive to change in load on said power turbine; valve means responsive to said load responsive means interposed between said inlet to said power turbine and said gen erating means for controlling the flow of gas to said power turbine to' increase and decrease said flow in the same sense as change in load; and valve-means responsive to said load responsive intermediatemeans interposed between an stage of said compressor turbine andsaid generatingi'means' forcontrolling. the direct flow of gas from said generating means to said intermediate stage to increase and decrease said flow in the opposite sense of change in load.

9. A gas turbine system, comprisingr'a combustion gas generating means having a fuelv inlet; a compressor delivering air to said generating. means; a multistage turbine drivingly connected withsaid compressor and having separate inlets for the first'and one or more intermediate stages thereof; an excess powerdeveloping. turbine; said compressor turbine and said power turbine 'having. separately rotatable driving shafts respectively; meansseverally connecting said separate inlets for the'first and one or more intermediate stages of said compressor turbine and the inlet to said power turbine directly with said generating means; means responsive to change in load on said power turbine; valve means responsive to said load responsive means interposed between said inlet to said power turbineand said generating means for controlling the flow of gas to said power turbine; valve means responsive to said load responsive means interposed between an intermediate stage of said compressor turbine and said generating means for controlling the direct flow of gas from said generating means to said intermediate stage; and valve means responsive to said loadresponsive means for controlling the flow through said fuel inlet. j

10. A gas turbine system, comprising: a-combustion gas generating means having a fuel in let;- a compressor delivering ai'r tosaid generat ing means; a multistage turbine drivingly con nected with said compressor and having separate inlets for the first and one or more intermediate stages thereof; an excess power developing turbine; said compressor turbine and said power turbine having separately rotatable driving shafts respectively; means severally connecting said separate inlets for the first and one or more intermediate stages of said compressor turbine and the inlet to said power turbine directly with said generating means; means responsive to change in load on said power turbine; means responsive directly and solely to said load responsive means for varying the flow of gas to said power turbine; means responsive to said load responsive means for varying the direct flow of gas to an intermediate stage of said compressor turbine; and means responsive to said load responsive means for varying the fiow through said fuel inlet.

11. A gas turbine system, comprising: a combustion gas generating means having a fuel inlet; a compressor delivering air to said generating means; a multistage turbine drivingly connected with said compressor and having separate inlets for the first and one or more intermediate stages thereof; an excess power developing turbine; said compressor turbine and said power turbine having separately rotatable driving shafts respectively; means severally connecting said separate inlets for the first and one or more intermediate stages of said compressor turbine and the inlet to said power turbine directly with said generating means; means responsive to change in load on said power turbine; means responsive directly and solely to said load responsive means for varying the flow of gas to said power turbine; means responsive to said load responsive means for varying the direct flow of gas to an intermediate stage of said compressor turbine; means responsive to said load responsive means for varying the flow through said fuel inlet; second load responsive means responsive to changes in load on said compressor turbine; and means responsive to said second load responsive means for varying the flow through said fuel inlet.

12. A gas turbine system, comprising: a combustion gas generating means having a fuel inlet; a compressor delivering air to said generating means; a turbine drivingly connected with said compressor; an excess power developing turbine; said compressor turbine and said power turbine having separately rotatable driving shafts; means severally connecting an inlet to said compressor turbine and an inlet to said power turbine with said generating means; means responsive to change in load on said power turbine; valve means associated with said power turbine inlet responsive directly and solely to said load responsive means for varying the flow of gas to said power turbine; and means responsive to said load responsive means for varying the flow through said fuel inlet.

13. A gas turbine system, comprising: a combustion gas generating means having a fuel inlet; a compressor delivering air to said generating means; a turbine drivingly connected with said compressor; an excess power developing turbine; said compressor turbine and said power turbine having separately rotatable driving shafts; means severally connecting an inlet to said compressor turbine and an inlet to said power turbine with said generating means; means responsive to change in load on said power turbine; valve means associated with said power turbine inlet and responsive to said load responsive means for varying the fiow of gas to said power turbine in the same sense as the change in load on said power turbine; second load responsive means responsive to the load on said compressor turbine;

and means responsive to said second load responsive means for varying the flow through said fuel inlet.

'14. A gas turbine system, comprising: a combustion gas generating means having a fuel inlet; a compressor delivering air to said generating means; a turbine drivingly connected with said compressor; an excess power developing turbine; said compressor turbine and said power turbine having separately rotatable driving shafts; means directly and severally connecting an inlet to said compressor turbine and an inlet to said power turbine with said generating means; means responsive to change in load on said power turbine; valve means associated with said power turbine inlet and responsive solely to said load responsive means for varying the flow of gas to said power turbine in the same sense as the change in load on said power turbine; means responsive to said load responsive means for varying the flow through said fuel inlet; second load responsive means responsive to changes in load on said compressor turbine; and means responsive to said second load responsive means for varying the flow through said fuel inlet.

15. A gas turbine system, comprising: a combustion gas generating means having a fuel inlet; a compressor delivering air to said generating means; a multistage turbine drivingly connected with said compressor and having separate inlets for the first and one or more intermediate stages thereof; an excess power developing turbine; said compressor turbine and said power turbine having separately rotatable driving shafts respectively; means d rectly and severally connecting said separate inlets for the first and one or more intermediate stages of said compressor turbine and the inlet to said power turbine with said generating means; means responsive to change in load on said power turbine; valve means associated with said power turbine inlet and responsive directly and solely to said load responsive means for varying the fiow of gas to said power turbine; valve means associated with at least one of said intermediate stage inlets and responsive to said load responsive means for varying the direct flow of gas to an intermediate stage of said compressor turbine; means responsive to said load responsive means for varying the flow through said fuel inlet; second load responsive means responsive to changes in load on said compressor turbine; and means responsive to said second load responsive means for varying the flow through said fuel inlet.

= JAMES L. RAY.

REFERENCES CITED The following references are of record in the file of this patent:

UNITED STATES PATENTS Number Name Date 2,095,991 Lysholm Oct. 19, 1937 2,225,310 Lindhagen Dec. 17, 1940 2,238,905 Lysholm Apr. 22, 1941 2,365,616 Zweifel Dec. 19, 1944 2,371,889 Hermitte Mar. 20, 1945