SU1394790A1 - Method of control of gas-turbine engine multi-stage compressor - Google Patents
Method of control of gas-turbine engine multi-stage compressorInfo
- 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
Links
Landscapes
- Control Of Positive-Displacement Air Blowers (AREA)
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
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 (1)
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 |
-
1986
- 1986-06-06 SU SU4075554/06A patent/SU1394790A1/en active
Cited By (1)
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 |
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