US1702264A

US1702264A - Gas turbine

Info

Publication number: US1702264A
Application number: US666648A
Authority: US
Inventors: Lorenzen Christian
Original assignee: Individual
Current assignee: Individual
Priority date: 1922-11-27
Filing date: 1923-10-04
Publication date: 1929-02-19
Anticipated expiration: 1946-02-19

Description

C. LORENZEN GAS TURBINE Feb. 19, 1929. r 1,702,264

Filed Oct- 4, 1925 3 Sheets-Sheet 1 [11 V0: for

Feb. 19, 1929. 1,702,264

c. LORENZEN GAS TURB INE Filed on. 4, 1923 3 Sheets-Sheet 2 Feb. 19,- 1929.

C. LORENZEN GAS TURBINE Filed Oct. 4, 1923 5 Sheets-Sheet -illllll III [n V611 Z 01" @M m me Feb. 19, 1929.

UNITED STATES CHRISTIAN LOBENZEN, F BERLIN-NEUKOLLIT, GERMANY.

,GAS TURBINE.

application filed. October 4, 1923, serial No.

The present invention relates to gas turbines of the type shown in my copending application Serial No. 50,274, filed August 14:, 1925, and in my Patent 1,640,784 ofAugust 30, 1927, wherein a cooling agent, such as air,

is passed through radial channels in the turbine blades, and is compressed by the cooperation of the rotating blades and a peripheral receptacle or diffuser.

An object of the invention is to obtain a high degree of cfiiciency and a thorough utilization of the heat content of the motive fluid. 7

In one form of the invention, the motive fluid is heated by the combustion of fuel in a combustion chamber, from which it passes to the turbine blades to impel them. The

power output of the turbine is derived almost solely from the kinetic energy of the motive fluid, which is caused to pass through the turbine at an effective driving velocity by transferring heat thereto in a heatexchanger and in the combustion chamber.

the turbine can be readily regulated by varying the fuel supply admitted to the combustion chamber, or by varying the pressure of the air entering the combustion chamber to support combustion therein.

The-present invention can be most advantageously employed with a low-speed turbinecompressor having comparatively large blades, to which the motive fluid is supplied in larger volume, but at lower velocity than in the ordinary turbine. The decrease in speed of the turbine lessens the stresses to which the moving parts are subjected, while.

the increase in the cross-sectional area of the bladesfacilitates cooling thereof, so that the cooling air, in passing through the blades does not reach a temperature approximating that of the power gases, and it is therefore possible to effect a further heat-exchange between the two fluids. The invention also comprises a'heat-exchanger for effecting such further heat-exchange. V

In a modified form of the invention, the air is circulated through a closed circuit which comprises a heater, a cooler, and the turbine-compressor. The invention is illustratcd'by way of example in the drawings, in which Fig. 1 is a diagrammatic view of the turbine-compressor and the heat-exchanger;

Fig. 2 shows a. modification wherein the motive fluid passes through a closed, circuit,

The output of.

666,648, and in Germany November 27, 1922.

Fig. 3 is a cross-sectional detail of the turbine blades; and r Fig. 4 is a further modification.

The heat-exchanger, shown in Fig. 1, is formed of two parallel sheets 1, 2, wound spiraily, and spaced apart to form two paths 3, 5,. for conducting the cold and hot gases respectively in opposite directions, as indicated by

arrows

4, 6. Radiation losses are minimized by first conducting the air to be heated around the exchanger, thereby forming an insulating jacket. Pipe 9, which conducts the heated air from path 3 to the combustion chamber 14, is also surrounded by a jacket 10 forming a heat insulation. The air in jacket 10 is preferably exhausted to enhance the heat-insulating properties of the jacket.

The heat-exchanger may also serve as a reservoir for air under pressure to housed in starting the turbine. For this purpose, a one-way valve 12 is placed in pipe 11, and a manually operable valve 13 is placed in pipe 9. When theturbine is to be Started, valve 13 is opened, allowing compressed air to flow from the heat-exchanger to the turbine to start it rotating. At the same time, the fuel valves16 are opened.

As ignition would not occur under the foregoing conditions, a small duct 16 is provided, to lead the compressed air from the blades, back through jacket 15 of the combustion chamber, and into the combustion chamberat the fuel nozzles 16, where it mingles with the fuel to support its combustion. The air is compressed by centrifugal action, as it asses outwardly in the direction indicated y the arrows, through compressor channels in the turbine rotor. The initial ignition of the'fuel is effected by introducing a match through an opening (not shown) or in any other well-known or approved manner. Combustion begins at the fuel-nozzles 16, sulficient air entering through 16, and a further supply of'air (which is heated) issues from the outlet of pipe 9, so that a thorough combustion is effected. Of course, the compressor and other parts are so proportioned that the air will be forced throughagainst any back pressura due to the heating of the air. When the turbine begins to operate, the pressure in theheat-exchanger has dro ped and the pressure caused by the turbine b ades has increased, so that valve 12 is automatically opened, allowing the compressed air to pass through pipe 11 to the heat-exchanger to be heated.

Referring to Fig. 2, at a point subjected as continuously and intensively as possible to the source of heat, for example, in the stack 17 for conducting off the heating or combustion gases of a technical plant, is located a pipe system 18. Air flows through this pipe system. The air enters in cold condition and with a certain speed of flow into the pipes, and

i is heated by the source of heat referred to.

The air thus heated flows through a piping 19 into the nozzle system 20, and out of the nozzles 20 into the blades 21 of the turbine rotor 22. After striking the turbine blades the air flows into a collecting chamber 23, from which, passing through a conduit 24, it reaches a pipe system 25 built into a cooling device, for example a feed water pre-heater 26. The air, which has already partially employed its energy of flow and its heat in the turbine, here discharges the remainder of its heat. After passing through-the pipe system 25 the air is sucked through a conduit 27 into the compressor 28, and forced through the passages 29 of the turbine blades 21 and the guide vane ring 30 into a collecting chamber 31, from which, proceeding through a conduit 32, it again reaches the pipe system 18.

Figure 4 shows a modified form of the invention, in which 33 represents a furnace having a grate 3-1 over an air induction means (not shown) Above the furnace 33, which is fed with fuel of'any desired kind, is located the point of utilization 35 of the plant, from which, for example, is fed a boiler, a chemical plant or the like. The waste gases from the plant pass over the point of utihzatlon through a pipe system 36 into the stack. With the plant is connected a turbine 37. This turbine is connected with the plant 33-36 by a conduit system 38, which passes in the direction of the arrow through the turbine into the top of the heat compensator of the plant 33-36. From the heat compensator the conduit proceeds towards the turbine, and out ofth'e turbine continues through one or two inlets 39, 4.0 into the furnace.

The working method of this plant is as follows: The furnace 33 is first set'into operation in the customary manner. The

inlets

39 and 40 are closed. The waste gases from the furnacefiow off through the heat compensator 36. The air located around the pipes of the heat compensator is thereby warmed. The normal air inlet for the combustion air for. thefurnace is now closed and the

openings

39 and 40 are opened. The furnace now sucks in the necessary combustion air throughthese openings. It thereby sets into operation the turbine 37, the details of which are contained in Figs. 3 and 4, and the above-described cycle of operations is developed, whereby the combustion air is sucked through the compressor 41, flows through the hollow turbine blades 42 I and the dilfusor 43 into the conduit 38, which conveys 1t to the-heat compensator 36. From here the air, substantially heated, reaches the turbine, and strikes against the blades thereof. The air loses in this manner a proportion of its heat, which is again subsequently attained in the form of compressed air. The majority of the heat remains in. the discharge air, and reaches the furnace with the discharge air of the turbine through the

openings

39 and 40. The temperature of same is thereby correspondingly increased, and the temperature accordingly increases at the point of utilization. In like manner the temperature of the waste gas is also increased. This, however, results in the fact that the fresh air in its circulation through the heat compensator is pre-heated to a substantial degree, i. e., enters with greater heat into the turbine, and after leaving the turbine sends' a greater heat through the

openings

39 and 40 into the furnace.

' In this manner the temperature at the utilization point of the furnace is continuously increased. This natural increase attains a limit at the point when the radiation'losses equalize the increase in temperature.

Certain features ofmy invention disclosed but not specifically claimed herein are claimed. in my Patent 1,601,402, granted September- 23, 1926, and for which an application was filed February 14, 1922, under Serial No.

What I claim is:

1. A gas turbine comprising a combustion chamber for supplying power gas to the ro under pressure in said heater for subsequently starting said turbine. 7

2. In a gas turbine, a rotor, a. combustion chamber for supplying a motive fluid to the rotor, blades on said rotor provided with radial passages, said passages being openat their inner ends to receive a cooling medium, the blades thereby forming a centrifugal compressor for said medium, a receiver communicating with the outer ends of said radial passages to receive the compressed cooling medium, a conduit extending between said receiver and said combustion chamber, a heatexchanger in said conduit, 11 valve between said receiver and heater, and a second valve between said heater and combustion chamber, said valves being adapted to retain said cooling agent under pressure in said heat-exchanger for starting the turbine.

3. In a gas turbine, a-rotor, a combustion chamber for supplying a motive fluid to the rotor, blades on'said rotor provided with radial passages, said passages being open at their inner ends to receive a cooling medium, the blades thereby forming a centrifugal compressor for said medium, a receiver communicating with the outer ends of said radial passages to receive the compressed cooling medium, a conduit extending from said receiver to said combustion'chamber, a heatexchanger in said conduit for transferring heat to said cooling agent, a one-way valve in said conduit between said receiver and said heat-exchanger, and a manually operable valve between said heat-exchanger and said combustion chamber.

4. A gas turbine comprising a combustion chamber for supplying power gas to the rotor of said turbine, hollow blades on said rotor to permit the passage of a cooling gas therethrough, means associated with said rotor for compressin said cooling gas, a heater having two paths for the cooling gas and the exhaust gas respectively, a conduit for conducting the exhaust gas from said rotor to one of said paths, :1 second conduit for conducting the cooling gas from said compressing means to the other of said paths, a third conduit leading from said heater to said com-- bustion chamber to supply heated compressed air thereto, and valves placed'in said second and third conduits whereby the cooling gas may be retained under pressure in said heater for subsequently starting said turbine.

'5. In a gas turbine, a rotor, a combustion chamber for supplying a motive fluid to the rotor, blades on said rotor provided with radial passages, said passages being open at their inner ends to receive a cooling medium, the blades thereby forming a centrifugal compressor .for said medium, a receiver communicating with the outer ends of said radial passages to receive the compressed cooling medium, a heat-exchanger having two paths, a conduit between said receptacle and one of said paths, a one-way valve in said conduit, a second conduit between the same path and the combustion chamber, a second valve in said second conduit, a normally open duct leading from said receptacle to said combustion chamber, and a conduit for conducting the exhaust motive fluid from said rotor to the other path of said heat-exchanger.

6. A gas turbine comprising a combustion chamber for supplying power gas to the retor of said turbine, said rotor being air cooled and rovided with means to compress the air usedhtor cooling it, a receptacle having an inlet opening adjacent the periphery of said rotor to receive compressed air from said rotor, a conduit leadin from said receptacle to said combustion chamber for supplying compressed combustion air thereto, a heater in said conduit, means for shutting ofi communication between said heater and said combustion chamber, and a duct leading directly from said receptacle to said combustion chamber.

7. A gas turbine comprising a rotor hav ing hollow blades permitting the passage of cooling gas therethrough, a combustion chamber for supplying power gas to said rotor, means associated with said rotor blades for compressing said cooling gas, a conduit connecting said means to said combustion chamber,a portion of said conduit forming one path of a heat exchange device, a conduit receiving the exhaust gases from said rotor and having a portion forming the other path of said heat exchan e device, and

valves in said first mentione conduit for shutting off the said portion from the remainder thereof.

In testimony whereof I have 'aflixed my signature.

CHRISTIAN LORENZEN.