US3469398A - Reignition system for jet engine - Google Patents

Reignition system for jet engine Download PDF

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Publication number
US3469398A
US3469398A US641957A US3469398DA US3469398A US 3469398 A US3469398 A US 3469398A US 641957 A US641957 A US 641957A US 3469398D A US3469398D A US 3469398DA US 3469398 A US3469398 A US 3469398A
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United States
Prior art keywords
engine
flame
jet engine
reignition
jet
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
US641957A
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English (en)
Inventor
Curtiss R Schafer
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.)
John Oster Manufacturing Co
Original Assignee
John Oster Manufacturing Co
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 John Oster Manufacturing Co filed Critical John Oster Manufacturing Co
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Publication of US3469398A publication Critical patent/US3469398A/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
    • F02C7/262—Restarting after flame-out

Definitions

  • the present invention relates to a system for detecting absence of flame in a jet engineand for reigniting the engine promptly upon detection of the loss of flame.
  • Another object of the invention is, therefore, to provide apparatus for promptly detecting the absence or decrease of ion content of the exhaust gases produced by a turbojet engine and for reigniting the jet engine immediately upon the occurrence of such a condition.
  • the invention has for another object the provision of an apparatus for automatically reigniting a jet engine immediately upon the occurrence of flameout.
  • a detecting apparatus responsive to the ion content of the exhaust gases produced by a turbojet engine.
  • This apparatus comprises one or more electrode arrays located at the exhaust or outlet end of the engine for developing an electrical current proportional to the product of the mass and velocity of the ions in the latter gases. If the ion content of the exhaust gases falls below a preselected minimum value an electrical signal is automatically supplied to a reignition circuit for igniting the jet engine.
  • a turbojet engine identified generally by the reference numeral 10 is there shown in somewhat diagrammatic form as comprising a housing or casing 11 containing a compressor 12 of conventional construction having its outlet 13 connected to deliver compressed gases to a combustion chamber 14 where the gases are heated and expanded for delivery to a turbine inlet 15.
  • the outlet 16 of the turbine is connected to a tailpipe inlet 17 located upstream from a conventional afterburner 18. Gases from the tailpipe flow through a tailpipe outlet 19 located downstream from the iafter burner and through a throat 20 to a jet nozzle out-
  • an electrode array is indicated generally by the reference numeral 22 and includes one or more electrodes.
  • each electrode assembly 23 is constructed as described in detail in the latter copending application wherein these assemblies have also been assigned the reference numeral 23.
  • the electrode assemblies develop an electrical current proportional to the ion concentration in the gases of the jet engine 10.
  • Each electrode assembly 23 is preferably mounted on the wall or casing 11 of the engine in the manner described in the copending application.
  • the num ber of electrodes in the array 22 is sufiicient to average out the effects of turbulence in the stream of exhaust gases.
  • the probes of the electrode assemblies are electrically connected in parallel so that their combined output is proportional to the sum of the ionization currents produced by the electrodes.
  • the parallel connected electrode assemblies 23 are electrically connected through conductor means 24 to a snap action regenerative or switching type amplifier 25 having its output connected to supply current to the operating coil 26a of a relay 26.
  • the electrodes may be selectively polarized to collect either negative or positive ions as desired.
  • the relay 26 includes a set of contacts 26b-26c for controlling application of power from a conventional AC source, such as a volt, 400 cycle source generally employed on aircraft, via conductors 27, 28 and 29 to an electrical ignition system or circuit 30.
  • a conventional AC source such as a volt, 400 cycle source generally employed on aircraft
  • the latter source also supplies power to a conventional DC power supply 31 via a conductor 32 and a common conductor 33 which is also connected to the ignition system 30 and to the amplifier 25.
  • the output of the ignition system is connected via a conductor 34 to one or more igniters or spark plugs 35.
  • the ion concentration in the exhaust gases causes the electrode array 22 to develop an input current to the amplifier 25 of suflicient value to create an output current for energizing the relay 26.
  • the relay 26 is energized so that its contacts 26b- 260 are open to break the circuit from the power supply conductors 27 and 28 to the ignition system conductor 29. If the engine flame is inadvertently extinguished, the ion concentration in the gases acting upon the electrode assemblies 23 immediately decreases sharply or disappears altogether so that the current developed by the 3 amplifier 25 is no longer suflicient to maintain the relay 26 energized.
  • the contacts 26b-26c thus revert to their normally closed position to complete the circuit from the power supply conductor 27 to the input of the ignition system 30 via the conductors 28 and 29.
  • the ignition system functions in well known manner in response to this application of power to develop an output for energizing the igniter 35, thereby to reignite the jet engine 10. Since the reignition occurs almost instantaneously after the flame has been extinguished, the rotor of the engine does not lose appreciable speed before the engine is reignited.
  • Capacitor discharge type units are used to provide the spark for the igniter or igniters 35. Such units require approximately one second to charge the capacitor sufficiently to the relay, the ignition system is automatically started.
  • the response time required for the detector or electrode array 22 to react to the loss of flame is 5 milliseconds or less
  • the response time of the amplifier 25 is 15 milliseconds or less
  • the response time of the relay is 7 milliseconds or less so that the total response is about 27 milliseconds or less. This means that the reignition may be started promptly after the flameout occurs and before sufficient time has passed to cause the rotor to decrease its speed below 9000 r.p.m.
  • a jet engine having means for producing a flame to maintain said engine in normal operation, said engine being subject to flame out, an ignition system for igniting said engine as a result of flame out, ion detecting means for detecting the ion content of exhaust gases and consequently the absence of flame in said engine after flame out, and means controlled by said detecting means for energizing said ignition system in response to the detection of absence of flame, said detecting means and energizing means being constructed and arranged to operate within a total time of about 27 milliseconds.
  • the detecting means comprises at least one electrode assembly for detecting the concentration of ions in the exhaust gases from the engine and operable to produce an indication within 5 milliseconds after the loss of flame.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Other Investigation Or Analysis Of Materials By Electrical Means (AREA)
US641957A 1967-05-29 1967-05-29 Reignition system for jet engine Expired - Lifetime US3469398A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US64195767A 1967-05-29 1967-05-29

Publications (1)

Publication Number Publication Date
US3469398A true US3469398A (en) 1969-09-30

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Family Applications (1)

Application Number Title Priority Date Filing Date
US641957A Expired - Lifetime US3469398A (en) 1967-05-29 1967-05-29 Reignition system for jet engine

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US (1) US3469398A (enrdf_load_stackoverflow)
FR (1) FR1579002A (enrdf_load_stackoverflow)
GB (1) GB1233241A (enrdf_load_stackoverflow)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4528844A (en) * 1982-12-28 1985-07-16 United Technologies Corporation Stall/debris discriminating ionic engine diagnostics
US4565969A (en) * 1983-04-29 1986-01-21 Aerochem Research Laboratories, Inc. Saturation current incipient soot detector
US4599568A (en) * 1982-12-28 1986-07-08 United Technologies Corporation Electrostatic afterburner light-off detector
US4713574A (en) * 1985-10-07 1987-12-15 The United States Of America As Represented By The Secretary Of The Air Force Igniter electrode life control
US4912921A (en) * 1988-03-14 1990-04-03 Sundstrand Corporation Low speed spool emergency power extraction system
US20020170294A1 (en) * 2001-02-22 2002-11-21 Marcel Stalder Thermal turbomachine and process for igniting the thermal turbomachine
WO2022152989A1 (fr) * 2021-01-15 2022-07-21 Safran Helicopter Engines Procédé et dispositif d'allumage

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4413303A (en) 1980-07-05 1983-11-01 Dunlop Limited Ignition systems
US20200284200A1 (en) * 2019-03-04 2020-09-10 Pratt & Whitney Canada Corp. Aircraft engine reignition

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2496502A (en) * 1947-03-11 1950-02-07 Wright Aeronautical Corp Ignition control system
US2689455A (en) * 1951-05-29 1954-09-21 Bendix Aviat Corp Electronic control apparatus for gas turbine engines
US2743577A (en) * 1952-06-02 1956-05-01 Phillips Petroleum Co Rocket engine control
US2820945A (en) * 1953-09-14 1958-01-21 Phillips Petroleum Co Flame turbulence analyzer

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2496502A (en) * 1947-03-11 1950-02-07 Wright Aeronautical Corp Ignition control system
US2689455A (en) * 1951-05-29 1954-09-21 Bendix Aviat Corp Electronic control apparatus for gas turbine engines
US2743577A (en) * 1952-06-02 1956-05-01 Phillips Petroleum Co Rocket engine control
US2820945A (en) * 1953-09-14 1958-01-21 Phillips Petroleum Co Flame turbulence analyzer

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4528844A (en) * 1982-12-28 1985-07-16 United Technologies Corporation Stall/debris discriminating ionic engine diagnostics
US4599568A (en) * 1982-12-28 1986-07-08 United Technologies Corporation Electrostatic afterburner light-off detector
US4565969A (en) * 1983-04-29 1986-01-21 Aerochem Research Laboratories, Inc. Saturation current incipient soot detector
US4713574A (en) * 1985-10-07 1987-12-15 The United States Of America As Represented By The Secretary Of The Air Force Igniter electrode life control
US4912921A (en) * 1988-03-14 1990-04-03 Sundstrand Corporation Low speed spool emergency power extraction system
US20020170294A1 (en) * 2001-02-22 2002-11-21 Marcel Stalder Thermal turbomachine and process for igniting the thermal turbomachine
US6729142B2 (en) * 2001-02-22 2004-05-04 Alstom Technology Ltd. Thermal turbomachine and process for igniting the thermal turbomachine
WO2022152989A1 (fr) * 2021-01-15 2022-07-21 Safran Helicopter Engines Procédé et dispositif d'allumage
FR3118994A1 (fr) * 2021-01-15 2022-07-22 Safran Helicopter Engines Procede et dispositif d’allumage
US12055101B2 (en) 2021-01-15 2024-08-06 Safran Helicopter Engines Ignition method and device

Also Published As

Publication number Publication date
GB1233241A (enrdf_load_stackoverflow) 1971-05-26
FR1579002A (enrdf_load_stackoverflow) 1969-08-22

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