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SU1394790A1 - Method of control of gas-turbine engine multi-stage compressor - Google Patents

Method of control of gas-turbine engine multi-stage compressor

Info

Publication number
SU1394790A1
SU1394790A1 SU4075554/06A SU4075554A SU1394790A1 SU 1394790 A1 SU1394790 A1 SU 1394790A1 SU 4075554/06 A SU4075554/06 A SU 4075554/06A SU 4075554 A SU4075554 A SU 4075554A SU 1394790 A1 SU1394790 A1 SU 1394790A1
Authority
SU
USSR - Soviet Union
Prior art keywords
combustion chamber
rotational speed
main combustion
gas
regulator
Prior art date
Application number
SU4075554/06A
Other languages
Russian (ru)
Inventor
В.П. Абруков
Original Assignee
В.П. Абруков
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 В.П. Абруков filed Critical В.П. Абруков
Priority to SU4075554/06A priority Critical patent/SU1394790A1/en
Application granted granted Critical
Publication of SU1394790A1 publication Critical patent/SU1394790A1/en

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Abstract

FIELD: aeronautical engineering. SUBSTANCE: according to the law of control, signals are generated in regulator 10 for feeding the required amount of fuel to main combustion chamber 3 and additional combustion chamber 4 and to actuating member 11 of air bypass passage 9. In nominal operating conditions, as well as in the operating conditions close to them, relationship of rotational speed of rotors is close to optimal and compressors possess required amount of stability. Actuating member 11 is switched on and shut-off device closes bypass passage 9. When main combustion chamber 3 is not in use or operates at low flow rate of fuel, error signal of rotor rotational speed reaches the magnitude preset by program and rotational speed of high-pressure turbocompressor rotor is reduced to preset value. Command is generated in regulator 10 for opening passage 9. Part of air fed to inlet of compressor 2 is bypassed to inlet of additional combustion chamber 4 past compressor, main combustion chamber 3 and high-pressure turbine 5. EFFECT: increased amount of gas-dynamic stability in transient conditions. 1 dwg
SU4075554/06A 1986-06-06 1986-06-06 Method of control of gas-turbine engine multi-stage compressor SU1394790A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
SU4075554/06A SU1394790A1 (en) 1986-06-06 1986-06-06 Method of control of gas-turbine engine multi-stage compressor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SU4075554/06A SU1394790A1 (en) 1986-06-06 1986-06-06 Method of control of gas-turbine engine multi-stage compressor

Publications (1)

Publication Number Publication Date
SU1394790A1 true SU1394790A1 (en) 1996-03-10

Family

ID=60535615

Family Applications (1)

Application Number Title Priority Date Filing Date
SU4075554/06A SU1394790A1 (en) 1986-06-06 1986-06-06 Method of control of gas-turbine engine multi-stage compressor

Country Status (1)

Country Link
SU (1) SU1394790A1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999047815A1 (en) * 1998-03-17 1999-09-23 Vladimir Iosifovich Belous Multi-stage axial compressor for aircraft engines
RU2172418C1 (en) * 2000-04-27 2001-08-20 Общевойсковая Академия Вооруженных Сил Российской Федерации Three-shaft gas-turbine engine
RU2370674C2 (en) * 2004-09-30 2009-10-20 Снекма Method of circulating air in turbine compressor, compressor exploiting this method, compressor stage of aforesaid design and aircraft engine incorporating said compressor

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1999047815A1 (en) * 1998-03-17 1999-09-23 Vladimir Iosifovich Belous Multi-stage axial compressor for aircraft engines
RU2165547C2 (en) * 1998-03-17 2001-04-20 Владимир Иосифович Белоус Aircraft engine multi-stage axial-flow compressor
RU2172418C1 (en) * 2000-04-27 2001-08-20 Общевойсковая Академия Вооруженных Сил Российской Федерации Three-shaft gas-turbine engine
RU2370674C2 (en) * 2004-09-30 2009-10-20 Снекма Method of circulating air in turbine compressor, compressor exploiting this method, compressor stage of aforesaid design and aircraft engine incorporating said compressor

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