US3858391A - Gas turbine starting circuit - Google Patents

Gas turbine starting circuit Download PDF

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Publication number
US3858391A
US3858391A US391786A US39178673A US3858391A US 3858391 A US3858391 A US 3858391A US 391786 A US391786 A US 391786A US 39178673 A US39178673 A US 39178673A US 3858391 A US3858391 A US 3858391A
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US
United States
Prior art keywords
starter
engine
amplifier
energized
control system
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US391786A
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English (en)
Inventor
James L Davis
Edward L Lopke
Louis W Huellmantel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Motors Liquidation Co
Original Assignee
General Motors Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Motors Corp filed Critical General Motors Corp
Priority to US391786A priority Critical patent/US3858391A/en
Priority to CA196,319A priority patent/CA1027214A/fr
Application granted granted Critical
Publication of US3858391A publication Critical patent/US3858391A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition

Definitions

  • a gas turbine power plant includes an electric starter for cranking the engine and an electrical control system, both energized from a storage battery.
  • the control system regulates the operation of the engine and includes a fuel valve solenoid and an atomizing air valve solenoid which are electrically energized. When the engine is started, these devices are energized along with the starter. Because of the heavy current required to operate the starter, the other electromagnetic devices are energized slightly before the starter to allow them to pull in while battery voltage is still at a normal level.
  • the control system is energized by a first relay and amplifier or driver circuit and the starter by a second relay and amplifier or driver circuit.
  • the starter amplifier circuit includes a capacitor which delays its operation for approximately 1/20 second after that of the other amplifier.
  • the system includes electromagnetic devices which are energized in order to enable operation of the engine and a starter which cranks the engine. These are concurrently energized from a common power source, but the energizing circuit of the starter includes delay means so that the other electromagnetic devices may pull in prior to the imposition of heavy current drain on the power source by the starter.
  • the principal objects of our invention are to improve the operation of gas turbine engines, to improve the starting characteristics and reliability of such engines, and to provide a simple starting circuit energizable through a single switch which delays energization of a starter until other electromagnetic devices have had time to pull in.
  • the FIGURE is a schematic diagram of a starting and control system for a gas turbine engine.
  • a conventionally represented gas turbine engine 2 may include a compressor 3, combustion apparatus 4, and a turbine or turbines 6.
  • Turbine 6 may drive a load such as a motor vehicle, for example.
  • the turbine or part of the turbine also drives compressor 3, which supplies air to the combustion apparatus to provide motive fluid for the turbine.
  • the engine is operated under control of an engine control system 7, the details of which are immaterial to the present invention except as may be explained subsequently.
  • Such control systems receive input of engine operating conditions and control operation of the engine through regulation of fuel or other conditions such as variable turbine nozzles and power transfer clutches, for example. Interconnections between the engine andcontrol are represented by the arrows 8 and 9.
  • control system is at least partly electrical orelectronic and includes electromag netic devices which must be energized to effect operation of the engine.
  • electromag netic devices which must be energized to effect operation of the engine.
  • Such devices energized through the control system 7 may include a solenoid 10 which opens a valve in the fuel line to the engine and a fuel atomizing air valve solenoid 11.
  • the operation of such solenoids, particularly the pull-in of such solenoids is sensitive to the available voltage, but once the solenoid is pulled in, thus opening the valve, they are relatively insensitive to the drop in battery output voltage caused by the heavy drain for operating the engine starter.
  • the electric starter 12 is indicated as connected to the engine through a suitable shaft 14.
  • the starter is energized only to crank the engine to self-sustaining speed, after which it is deenergized and effectivelydisconnected from the engine.
  • Switch 16 may correspond to the ordinary ignition and start switch of a vehicle and is opened to stop the engine and closed to cause the engine to run.
  • switch When the switch is closed and bus 18 is energized, it provides a source of power for a run relay driver or amplifier I9 and a starter relay driver or amplifier 20. These energize, respectively, the coils 22 of a run relay 23 and the coil 24 of a starter relay 26.
  • run relay 23 When the run relay 23 is energized, it closes contact 27 to deliver power to the engine control system 7 including solenoids 10 and 11.
  • the starter relay coil 24 When the starter relay coil 24 is energized, it closes contact 28 to deliver power from the battery 15 to the starter motor 12.
  • Both the run relay amplifier 19 and starter relay amplifier 20 are energized, when switch 16 is closed, through a normally closed RumStop switch 30.
  • This switch is opened to stop the engine. It may be manually actuated and may also respond to engine overspeed, overtemperature, or other unsatisfactory operating conditions of the engine sensed by the control system 7, as is well known.
  • the starter amplifier is also energized through a Starter Cutout switch 31 which is closed initially and remains closed until the engine has been started, at which time this switch is opened by the control system 7 to terminate operation of the starter and remains open until the engine is stopped and a new starting cycle is initiated, as is generally understood.
  • the amplifiers 19 and 20 are connected between the bus 18, energized at a nominal 12 volts from battery 15 when switch 16 is closed, and a ground or return bus 32.
  • run relay amplifier 19 when switch 16 is closed a circuit is completed from bus 18 through normally closed Run-Stop switch 30 and a voltage divider comprising series resistors 34 and 35 (both of 10 kilohms) to ground.
  • the junction of these resistors is connected to the base of an NPN transistor 36 (Delco Service No. 67).
  • Theemitter of transistor 36 is connected to ground bus 32 through one kilohm resistor 38 and its collector is connected to bus 18 through a 470 ohm one watt resistor 39.
  • Tlie'emitter of transistor 36 is connected to the base of an NPN transistor 40 (type 2N5183). This transistor has its emitter connected to ground bus 32 and its collector through relay coil 22 to bus 18. When switch 16 is closed, the base of transistor 36 is raised to approximately 1.5 volts which turns it on, and the resulting drop through resistor 38 turns on transistor 40, the base current of which flows through transistor36. Relay 23, thus energized, closes contact 27 to supply 12 volts of power to the engine control system 7.
  • the emitter-collector circuit of transistor 40 is shunted by a diode 42 (Delco Service Type 31).
  • a diode 42 (Delco Service Type 31).
  • the starter amplifier 20 is identical to amplifier 19 except for the provision for time delay and for heavier duty components in the output circuit to handle the heavier current demand of the starter relay 26.
  • elements 34, 35, 36, 38 and 39' duplicate the corresponding elements of amplifier 19.
  • the power transistor 44 is Delco Service type 513 and the diode 46 is Delco Service type 79. It can be seen that the circuit connections for these are the same as the other amplifier.
  • the additional element of amplifier 20 is a 50 mfd delay capacitor 48 connected in parallel with resistor 35'. With this circuit, when switch 16 is closed and current flows through switches 30 and 31 and resistor 34, the potential rise across resistor 35 follows an exponential curve as capacitor 48 charges. The charging time of the capacitor is such that the base of transistor 36' reaches its turn-on voltage after a delay of approximately 1/20 second. Otherwise, amplifier 20 operates the same as amplifier 19.
  • a motor vehicle the combination of a gas turbine engine, an electrically-energized starter for cranking the engine, a control system for the engine including electromagnetic devices energized during starting and operation of the engine, and a storage battery for energizing the control system and starter with first relay means connected to energize the said control means from the battery, second relay means connected to energize the starter from the battery, and common energizing means for simultaneously energizing the said relay means, in which the second relay means includes time delay means to allow energization and pull-in of the said electromagnetic devices prior to energization of the starter and the accompanying drop in battery output voltage.
  • a gas turbine engine an electrically-energized starter for cranking the engine
  • a control system for the engine including electromagnetic devices energized during starting and operation of the engine
  • a storage battery for energizing the control system and starter with first relay means connected to energize the said control means from the battery including a first amplifier, second relay means connected to energize the starter from the battery including a second amplifier, and common energizing means for simultaneously energizing the said amplifiers, in which the second amplifier includes time delay capacitor means to delay operation of the second amplifier and thus allow energization and pull-in of the said electromagnetic devices prior to energization of the starter and the accompanying drop in battery output voltage.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)
US391786A 1973-08-27 1973-08-27 Gas turbine starting circuit Expired - Lifetime US3858391A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US391786A US3858391A (en) 1973-08-27 1973-08-27 Gas turbine starting circuit
CA196,319A CA1027214A (fr) 1973-08-27 1974-03-29 Circuit de demarrage d'une turbine a gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US391786A US3858391A (en) 1973-08-27 1973-08-27 Gas turbine starting circuit

Publications (1)

Publication Number Publication Date
US3858391A true US3858391A (en) 1975-01-07

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Family Applications (1)

Application Number Title Priority Date Filing Date
US391786A Expired - Lifetime US3858391A (en) 1973-08-27 1973-08-27 Gas turbine starting circuit

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US (1) US3858391A (fr)
CA (1) CA1027214A (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3938320A (en) * 1974-07-17 1976-02-17 General Motors Corporation Starting system for a helicopter power plant control
US4329951A (en) * 1979-04-21 1982-05-18 Lucas Industries Limited Fuel injection system
DE4015885A1 (de) * 1990-05-17 1991-11-21 Bmw Rolls Royce Gmbh Startvorrichtung fuer anlasser an turbinentriebwerken
US6256977B1 (en) 1999-09-07 2001-07-10 Alliedsignal, Inc. Start circuit for electric starting of engines
US20070234739A1 (en) * 2005-09-20 2007-10-11 Honeywell International, Inc. Gas turbine engine cold start mechanization
US9611752B2 (en) 2013-03-15 2017-04-04 General Electric Company Compressor start bleed system for a turbine system and method of controlling a compressor start bleed system

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2886015A (en) * 1956-10-26 1959-05-12 Bosch Gmbh Robert Fuel injection arrangement
US2962597A (en) * 1959-06-09 1960-11-29 Westinghouse Electric Corp Power plant apparatus
US3310937A (en) * 1965-08-20 1967-03-28 Avco Corp Automatic starting control system for gas turbine engines
US3440433A (en) * 1966-05-19 1969-04-22 Bendix Corp Aircraft starter control
US3443112A (en) * 1965-12-09 1969-05-06 Gen Motors Corp Electric cranking motor automatic disconnect circuit
US3691759A (en) * 1971-01-14 1972-09-19 Curtiss Wright Corp Automatic control system for a turbojet engine employed in a stationary environment

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2886015A (en) * 1956-10-26 1959-05-12 Bosch Gmbh Robert Fuel injection arrangement
US2962597A (en) * 1959-06-09 1960-11-29 Westinghouse Electric Corp Power plant apparatus
US3310937A (en) * 1965-08-20 1967-03-28 Avco Corp Automatic starting control system for gas turbine engines
US3443112A (en) * 1965-12-09 1969-05-06 Gen Motors Corp Electric cranking motor automatic disconnect circuit
US3440433A (en) * 1966-05-19 1969-04-22 Bendix Corp Aircraft starter control
US3691759A (en) * 1971-01-14 1972-09-19 Curtiss Wright Corp Automatic control system for a turbojet engine employed in a stationary environment

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3938320A (en) * 1974-07-17 1976-02-17 General Motors Corporation Starting system for a helicopter power plant control
US4329951A (en) * 1979-04-21 1982-05-18 Lucas Industries Limited Fuel injection system
DE4015885A1 (de) * 1990-05-17 1991-11-21 Bmw Rolls Royce Gmbh Startvorrichtung fuer anlasser an turbinentriebwerken
US6256977B1 (en) 1999-09-07 2001-07-10 Alliedsignal, Inc. Start circuit for electric starting of engines
US20070234739A1 (en) * 2005-09-20 2007-10-11 Honeywell International, Inc. Gas turbine engine cold start mechanization
US7690205B2 (en) 2005-09-20 2010-04-06 Honeywell International Inc. Gas turbine engine cold start mechanization
US9611752B2 (en) 2013-03-15 2017-04-04 General Electric Company Compressor start bleed system for a turbine system and method of controlling a compressor start bleed system

Also Published As

Publication number Publication date
CA1027214A (fr) 1978-02-28

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