IL258770B2 - Method of controlling of turbocharging of aircraft engine - Google Patents

Method of controlling of turbocharging of aircraft engine

Info

Publication number
IL258770B2
IL258770B2 IL258770A IL25877018A IL258770B2 IL 258770 B2 IL258770 B2 IL 258770B2 IL 258770 A IL258770 A IL 258770A IL 25877018 A IL25877018 A IL 25877018A IL 258770 B2 IL258770 B2 IL 258770B2
Authority
IL
Israel
Prior art keywords
engine
turbocharger
compressor
turbine
combustion
Prior art date
Application number
IL258770A
Other languages
Hebrew (he)
Other versions
IL258770A (en
IL258770B (en
Inventor
Zhmudyak Leonid
Zhmudyak Alexandra
Original Assignee
Zhmudyak Leonid
Zhmudyak Alexandra
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 Zhmudyak Leonid, Zhmudyak Alexandra filed Critical Zhmudyak Leonid
Priority to IL258770A priority Critical patent/IL258770B2/en
Publication of IL258770A publication Critical patent/IL258770A/en
Publication of IL258770B publication Critical patent/IL258770B/en
Publication of IL258770B2 publication Critical patent/IL258770B2/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/04—Engines with exhaust drive and other drive of pumps, e.g. with exhaust-driven pump and mechanically-driven second pump
    • F02B37/10—Engines with exhaust drive and other drive of pumps, e.g. with exhaust-driven pump and mechanically-driven second pump at least one pump being alternatively or simultaneously driven by exhaust and other drive, e.g. by pressurised fluid from a reservoir or an engine-driven pump
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B37/00—Engines characterised by provision of pumps driven at least for part of the time by exhaust
    • F02B37/04—Engines with exhaust drive and other drive of pumps, e.g. with exhaust-driven pump and mechanically-driven second pump
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Supercharger (AREA)

Description

B64D 31/00 METHOD OF CONTROLLING OF TURBOCHARGING OF AIRCRAFT ENGINE Description FIELD OF THE INVENTION The invention relates to a turbocharged piston internal combustion engine (PICE), which operate at high altitude. In particular, the invention relates to an aircraft’s engines.
BACKGROUND OF THE INVENTION The prototype of the present invention is a conventional aircraft engine with a turbocharger (here and below the turbocharger for brevity is denoted: "TC"). The engine can be both diesel or gasoline spark ignition engine. The prototype engine may have an intercooler.When the aircraft flies to a high altitude the engine power decreases. (The "high" is the altitude at which a decrease in air density leads to a significant decrease in engine power.) Here we mean the engine power and the operation of the turbocharger, including the degree of pressure increase in the compressor, at full loads. [Under full loads we mean the modes of operation with a fuel supply close to the nominal and maximum (these modes include the maximum torque regime), as well as modes with the specified fuel supply and high speed, which include revolutions close to the rated and maximum revs, as well as the speed of torque. "Close" refers to quantities that differ by 25% more or less.]Low air density can lead the turbocharger to an off-design behavior, hence decrease in compression ratio of the compressor.All the above, including the drop at the turbocharger speed, the compression ratio of the air in the compressor and the engine power, applies fully to the two-stage supercharged engine as well as to the engine with the wave pressure exchanger (comprex).
BRIEF DESCRIPTION OF THE DRAWING Figure schematically shows the engine with the turbocharger. There is the bypass channel, which connects the compressor and turbine of the turbocharger and the combustion chamber connected to this channel.

Claims (8)

1.CLAIMS What is claimed is: Claim 1. A method of controlling the turbocharging of an engine, having a bypass channel between a compressor and a turbine of a turbocharger, including combustion of fuel in a combustion chamber located in the bypass channel, wherein the method is used in an aircraft engine or air machine engine at full load while for purpose of recovering and/or increasing power as the flight altitude increases and when flying at the high flight altitude, where the air density drops, said combustion of fuel is executed at full load.
2.Claim 2. The method according to claim 1 or 2, wherein the method is carried out in aircraft take-off and/or in the maximum engine power mode, meaning the maximum power if it needs in emergency situations.
3.Claim 3. The method according to claim 1 or 2, wherein an additional compressor is used, said compressor is installed after the compressor of the turbocharger and is driven by the engine crankshaft or an external power source, for example, an electric motor, a compressed-air bottle, etc. and turns on when it is necessary to increase the engine power in situations: flight at high altitude, the flight altitude increases, aircraft take-off, emergency situations, engine start and in conditions where the pressure before the turbine of the turbocharger is equal to or higher than the pressure after the compressor of the turbocharger and/or when the turbocharger stopped or has not yet running.
4.Claim 4. The method according to any one of claims 1 to 3, wherein a valve prevents the flow of gases through the bypass channel in the opposite direction: from the turbine to the compressor.
5.Claim 5. The method according to any one of claims 1 to 4, wherein an electric motor or a mechanical connection to the engine is used to start, for initial rotation, and/or to increase the turbocharger speed.
6.Claim 6. The method according to any one of claims 1 to 5, wherein the combustion chamber is a pulsejet engine or pulse detonation engine, for such combustion chamber other terms are also used: a chamber of constant volume, a chamber of periodic combustion.
7.Claim 7. The method according to claims 1 to 6, wherein in the engine, having a two-stage turbocharging, the bypass channel is connected to a low-pressure turbine.
8.Claim 8. The method according to claims 1 to 7, wherein in the air, entering the combustion chamber, prior to entering is heated by the heat of the exhaust gases.
IL258770A 2018-04-17 2018-04-17 Method of controlling of turbocharging of aircraft engine IL258770B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
IL258770A IL258770B2 (en) 2018-04-17 2018-04-17 Method of controlling of turbocharging of aircraft engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
IL258770A IL258770B2 (en) 2018-04-17 2018-04-17 Method of controlling of turbocharging of aircraft engine

Publications (3)

Publication Number Publication Date
IL258770A IL258770A (en) 2018-05-31
IL258770B IL258770B (en) 2022-12-01
IL258770B2 true IL258770B2 (en) 2023-04-01

Family

ID=62454983

Family Applications (1)

Application Number Title Priority Date Filing Date
IL258770A IL258770B2 (en) 2018-04-17 2018-04-17 Method of controlling of turbocharging of aircraft engine

Country Status (1)

Country Link
IL (1) IL258770B2 (en)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4215550A (en) * 1977-02-17 1980-08-05 Motoren- Und Turbinen-Union Friedrichshafen Gmbh Supercharged internal combustion engine and method of operation thereof
FR2491996A1 (en) * 1980-10-10 1982-04-16 Inst Francais Du Petrole Overfeed for turbocharged IC-engine - has auxiliary compressor to pass extra air to turbocharger turbine
EP0782663B1 (en) * 1994-08-25 2000-11-02 James Neville Randle Turbocharged internal combustion engine arrangement

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4215550A (en) * 1977-02-17 1980-08-05 Motoren- Und Turbinen-Union Friedrichshafen Gmbh Supercharged internal combustion engine and method of operation thereof
FR2491996A1 (en) * 1980-10-10 1982-04-16 Inst Francais Du Petrole Overfeed for turbocharged IC-engine - has auxiliary compressor to pass extra air to turbocharger turbine
EP0782663B1 (en) * 1994-08-25 2000-11-02 James Neville Randle Turbocharged internal combustion engine arrangement

Also Published As

Publication number Publication date
IL258770A (en) 2018-05-31
IL258770B (en) 2022-12-01

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