US2305311A - Gas turbine plant equipped with regulating apparatus - Google Patents

Gas turbine plant equipped with regulating apparatus Download PDF

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Publication number
US2305311A
US2305311A US217506A US21750638A US2305311A US 2305311 A US2305311 A US 2305311A US 217506 A US217506 A US 217506A US 21750638 A US21750638 A US 21750638A US 2305311 A US2305311 A US 2305311A
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Prior art keywords
working medium
compressor
gas turbine
lever
blades
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Expired - Lifetime
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US217506A
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English (en)
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Jendrassik George
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Individual
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line

Definitions

  • Proposals for the regulationof gas turbines are known according to which, in order to keep the 'tempe'r'atureof the gas turbineplant at a suitable figure at diminishing outputs, provision is made,'simultaneously with the'diminution of the quantity of fuel burntper revolution, for diminishing also, by throttlingthe suction pressure of the compressor compressing the working medium, the quantity of airsuppliedby the compressor, in consequence whereof. the temperature of the working medium expanding in the turbine need not be diminished in' case of diminishing output either.
  • a very great drawback of these proposals consists in the fact that-the throttling employed in the suction duct.
  • the losses bearing any relation to the: magnitude of the quantity of air, e. g..thelossees of the heat exchange device serving for heating the compressed working medium 'and'for'cooling down the gases leaving the turh-ine will also diminish.
  • Particularly suitable for performing the regulation will be a type of compressor in which the mean diameter of any stationary or rotating blade ring will, at least approximately, be equal to 'the average of the mean diameters of the two blade rings adjacent to it,
  • the regulating apparatus forming the subject of the invention eliminates this drawback in such a manner that it ma'kes provision, in the case of the working medium, of the blades which is di-' v minished, and therefore such deflection influcences'the efllciency of,- the stage or of stages in question but does "not cause any extra loss. It will be preferable to vary the quantity of fuel introduced and the quantity of air supplied by the compressor in such a manner as toensure that the temperature of the working medium entering any stage of the turbineshould remain unchanged also with widely varying outputs; this will enable the thermal efficiency of the plant to be kept at a high figure at low outputs also.
  • the deflection of the blades of the compressor will exert a double effect; on the one hand it will tend to reduce the proportion of pressures produced in the stage in question, and on the other hand-in so far as the deflection of the blades in'the case of diminishing'outputs takes place so as to start from the low-pressure stages of the compressor-it will also tend to reduce the volume drawn in by the compressor.
  • This latter method of regulation is more advantageous, as in around the pivot I0 is engaging.
  • Fig. 1 shows the deflection of the blades being effected by means of a speed governor
  • Fig. 2 shows the performance of the same deflection by means of a thermostat.
  • Figs. 3 and 4 exemplify a mechanism serving for the performance of the deflection of the blades
  • Fig. 5 illustrates, in cross-section, the fuel nozzle and the combustion chamber of the gas turbine in the case of its being fed with liquid fuel.
  • the oscillating masses 5 and 6 of the centrifugal governor are able to oscillate around the pivots I, I and are supported by means of lever transmissions on the sleeve 8 of the governor, on which sleeve the spring 9 is also acting. It is with the sleeve 8 that the lever II journalled This lasted with the lever I3, which operates a mechanism, shown in Figs. 3 and 4, for deflecting the blades of the compressor.
  • Fig. 3 shows the axial section of the blade rings of'the compressor, the said section being taken through the pivot 39 of the lever I3
  • Fig. 4 shows the view, developed into a plane of the mechanis'memployed for deflecting the blades.
  • the arrangement as shown by way of example is one in which it is the blades of the blade ring 31 of the pressure stage of lowest pressure, i. e.
  • which belongs to the sense of rotation 43 (corresponding to diminishing output) of the lever I3 is marked 45, whilst the sense of deflection of the pivots 39 and thereby of the blades 31' corresponding to the sense of rotation 43 of the lever I3 is marked 44.
  • the compressor draws in the working medium through the tube
  • the compressed working medium discharged from the compressor is preferably led through the heat exchange device IS, in which it is heated by means of the gases discharged from the turbine to nearly the temperature of the latter.
  • the working medium After heat transmission the working medium expands in the turbine and leaves the latter through the duct I9, from which it passesv into the heat exchange device ii, in which latter it becomes its contents of heat cooled down, transmitting to the fresh quantity of working medium, and will leave the plant through the duct 20.
  • reacting on the temperature of the working medium is arranged so as to be in contact with the working medium entering the turbine.
  • this thermostat is constructed as a gas thermometer
  • the nozzle body contains the needle valve 41 on the free end projecting from the nozzle body of which the lever 29 acts in a direct manner.
  • the valve rod of the needle valve possesses a threaded part 48 with the aid of which the needle-valve can be displaced in its axial direction in the thread cut into the nozzle body when operating the lever 29 and thereby the opening of the needle valve may be made smaller or greater (smaller if the temperature acting on the thermostat rises) so as to suit the conditions of operation.
  • is keeping the temperature of the working medium more or less constant owing to the fact that any possible increase of the temperature will cause the membrane of the thermostat to become displaced under the action of the rise of pressure taking place in the interior of the thermostat, which pressure is transmitted by the rod 25, the doublearm lever 21 and the pull-rod 28 to the lever 29, thereby influencing the quantity of heat introduced into the working medium in the direction of diminishing the said quantity.
  • which ensures that the fluctuation of the temperature of the working medium should not exceed the amount of variations permitted, whilst the centrifugal governor 4 ensures that the number of revolutions per minute of the set of machinery should not'exceed the permitted limits.
  • the centrifugal governor 4 will with the aid of the lever H and of the pull-rod l2 adjust the lever
  • This stage of regulation will, whilst keeping the quantity of fuel introduced unchanged, cause a rise of temperature in the vicinity of the thermostat,
  • thermostat will become operative and will diminish the quantity of fuel burnt.
  • the embodiment shown by way of example in Fig. 2 differs from the preceding one only in so far that there it is not the quantity of heat that is regulated by the thermostat 2
  • the centrifugal governor 4 exerts through the lever 34 a regulating action on the quantity of fuel burnt.
  • the course of regulation in the case of diminishing load is the following: The centrifugal governor 4 diminishes, by means of the pull-rod 33 and of the lever 34, the quantity of heat introduced. Thereby the temperature in the vicinity of the thermostat 2
  • the thermostat will, through the lever 3
  • fary compressor compressing the working medium for the gas turbine means introducing heat by fuel combustion into the compressed working medium, a thermostat, reacting on temperature,
  • a device regulating the quantity of fuel to be burnt being operatively connected with the said'thermostat, a device suitable for deflecting the stationary blades of at least some stages of the compressor, and a speed governor reacting on the number of revolutions P. M. of the turbine, being operatively connected with the said device suitable for deflecting the compressor blades in such a manner that in case of increasing number of revolutions the angle of attack of the deflected blades should be diminished.
  • deflected blades should also be diminished.
  • a gas turbine In a gas turbine plant, a gas turbine, a rotary compressor compressing the working medium for the gas turbine, means introducing heat by fuel combustion into the compressed working medium, a thermostat, reacting on temperature variations, in contact with the previ-' ously heated working medium of the gas turbine, a device regulating the quantity of fuelto be burnt, a device suitable for deflecting the sta- 2.
  • a gas turbine In a gas turbine plant, a gas turbine, a rotary compressor compressing the working medium for the gas turbine, means introducing heat by fuel combustion into the compressed working medium, a thermostat, reacting on temperature variations, in contact with the previously heated working medium of the gas turbine, a device regulating the quantity of fuel to be burnt, a speed governor reacting on the numtionary blades of at least some stages of the compressor, and a speed governor reacting on the number of revolutions P. M.
  • the said thermostat being operatively connected with the one, and the said speed governor with the other of the said devices suitable for deflecting the blades and for regulating the fuel quantity in such a manner that in case of diminishing output theangle of attack of the deflected blades should be, together with the diminution of fuel supply, diminished.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
US217506A 1937-07-07 1938-07-05 Gas turbine plant equipped with regulating apparatus Expired - Lifetime US2305311A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
HU2305311X 1937-07-07

Publications (1)

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US2305311A true US2305311A (en) 1942-12-15

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US217506A Expired - Lifetime US2305311A (en) 1937-07-07 1938-07-05 Gas turbine plant equipped with regulating apparatus

Country Status (2)

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US (1) US2305311A (fr)
FR (1) FR840427A (fr)

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2428830A (en) * 1942-04-18 1947-10-14 Turbo Engineering Corp Regulation of combustion gas turbines arranged in series
US2473356A (en) * 1942-04-18 1949-06-14 Turbo Engineering Corp Combustion gas turbine arrangement
US2527732A (en) * 1946-02-07 1950-10-31 Rateau Soc Braking device for aircraft jet turbopropellers
US2532469A (en) * 1945-08-13 1950-12-05 Bendix Aviat Corp Airplane control system
US2581275A (en) * 1944-10-09 1952-01-01 Bendix Aviat Corp Fuel feed responsive to air pressure and temperature, fuel flow, and speed for gas turbines
US2631428A (en) * 1946-08-28 1953-03-17 Arthur H Nelson Multiple fluid-operated rotary gear motors with treatment between stages
US2641324A (en) * 1943-02-19 1953-06-09 Bristol Aeroplane Co Ltd Regulating means for gas turbine installations
US2697326A (en) * 1951-04-30 1954-12-21 Ca Nat Research Council Reactor with adjustable stator blades
US2933234A (en) * 1954-12-28 1960-04-19 Gen Electric Compressor stator assembly
US2936108A (en) * 1957-04-29 1960-05-10 Gen Electric Compressor
US2936578A (en) * 1954-05-06 1960-05-17 United Aircraft Corp Variable orifice type jet nozzle
US2980394A (en) * 1956-11-23 1961-04-18 Garrett Corp Temperature responsive variable means for controlling flow in turbomachines
US3053086A (en) * 1957-02-12 1962-09-11 Granberg Corp Turbine type meter
US3079127A (en) * 1956-11-23 1963-02-26 Garrett Corp Temperature responsive variable means for controlling flow in turbomachines
US3146626A (en) * 1959-09-19 1964-09-01 Voith Gmbh J M Adjusting mechanism for blades of fluid flow machines, especially torque converters
US3356288A (en) * 1965-04-07 1967-12-05 Gen Electric Stator adjusting means for axial flow compressors or the like
US3647312A (en) * 1969-02-20 1972-03-07 Ckd Praha Mounting of stator blades in axial compressors
US3954349A (en) * 1975-06-02 1976-05-04 United Technologies Corporation Lever connection to syncring
EP0393531A1 (fr) * 1989-04-21 1990-10-24 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Dispositif pour la variation du calage des aubes de stator
EP0909880A3 (fr) * 1997-10-14 2000-02-23 General Electric Company Système d'actionnement des aubes de guidage pour turbines
US6328526B1 (en) * 1999-04-02 2001-12-11 Mitsubishi Heavy Industries, Ltd. Gas turbine starting method
EP1469166A1 (fr) * 2003-04-16 2004-10-20 Snecma Moteurs Dispositif de commande d'aubes à calage variable dans une turbomachine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4133567A (en) * 1977-05-11 1979-01-09 Texaco Inc. Combined cycle electric power generating system with improvement
DE3514354A1 (de) * 1985-04-20 1986-10-23 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Gekuehlte gasturbine mit lastabhaengig regelbarer kuehlluftmenge

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2428830A (en) * 1942-04-18 1947-10-14 Turbo Engineering Corp Regulation of combustion gas turbines arranged in series
US2473356A (en) * 1942-04-18 1949-06-14 Turbo Engineering Corp Combustion gas turbine arrangement
US2641324A (en) * 1943-02-19 1953-06-09 Bristol Aeroplane Co Ltd Regulating means for gas turbine installations
US2581275A (en) * 1944-10-09 1952-01-01 Bendix Aviat Corp Fuel feed responsive to air pressure and temperature, fuel flow, and speed for gas turbines
US2532469A (en) * 1945-08-13 1950-12-05 Bendix Aviat Corp Airplane control system
US2527732A (en) * 1946-02-07 1950-10-31 Rateau Soc Braking device for aircraft jet turbopropellers
US2631428A (en) * 1946-08-28 1953-03-17 Arthur H Nelson Multiple fluid-operated rotary gear motors with treatment between stages
US2697326A (en) * 1951-04-30 1954-12-21 Ca Nat Research Council Reactor with adjustable stator blades
US2936578A (en) * 1954-05-06 1960-05-17 United Aircraft Corp Variable orifice type jet nozzle
US2933234A (en) * 1954-12-28 1960-04-19 Gen Electric Compressor stator assembly
US3079127A (en) * 1956-11-23 1963-02-26 Garrett Corp Temperature responsive variable means for controlling flow in turbomachines
US2980394A (en) * 1956-11-23 1961-04-18 Garrett Corp Temperature responsive variable means for controlling flow in turbomachines
US3053086A (en) * 1957-02-12 1962-09-11 Granberg Corp Turbine type meter
US2936108A (en) * 1957-04-29 1960-05-10 Gen Electric Compressor
US3146626A (en) * 1959-09-19 1964-09-01 Voith Gmbh J M Adjusting mechanism for blades of fluid flow machines, especially torque converters
US3356288A (en) * 1965-04-07 1967-12-05 Gen Electric Stator adjusting means for axial flow compressors or the like
US3647312A (en) * 1969-02-20 1972-03-07 Ckd Praha Mounting of stator blades in axial compressors
US3954349A (en) * 1975-06-02 1976-05-04 United Technologies Corporation Lever connection to syncring
EP0393531A1 (fr) * 1989-04-21 1990-10-24 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Dispositif pour la variation du calage des aubes de stator
US5035572A (en) * 1989-04-21 1991-07-30 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Arrangement for adjusting guide blades
EP0909880A3 (fr) * 1997-10-14 2000-02-23 General Electric Company Système d'actionnement des aubes de guidage pour turbines
US6328526B1 (en) * 1999-04-02 2001-12-11 Mitsubishi Heavy Industries, Ltd. Gas turbine starting method
EP1469166A1 (fr) * 2003-04-16 2004-10-20 Snecma Moteurs Dispositif de commande d'aubes à calage variable dans une turbomachine
FR2853930A1 (fr) * 2003-04-16 2004-10-22 Snecma Moteurs Dispositif de commande d'aubes a calage variable dans une turbomachine

Also Published As

Publication number Publication date
FR840427A (fr) 1939-04-25

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