12 research outputs found
Numerical analysis of the turbomachine blade row aeroelastic oscillations with taking into account the disc deformation
ΠΠ΅ΡΡΠ°ΡΠΈΠΎΠ½Π°ΡΠ½ΡΠ΅ ΡΠ²Π»Π΅Π½ΠΈΡ, Π²ΡΠ·Π²Π°Π½Π½ΡΠ΅ ΠΊΠΎΠ»Π΅Π±Π°Π½ΠΈΡΠΌΠΈ Π»ΠΎΠΏΠ°ΡΠΎΠΊ ΠΏΠΎΠ΄ Π΄Π΅ΠΉΡΡΠ²ΠΈΠ΅ΠΌ Π²ΠΎΠ·ΠΌΡΡΠ°ΡΡΠΈΡ
ΡΠΈΠ», Ρ
Π°ΡΠ°ΠΊΡΠ΅ΡΠΈΠ·ΡΡΡΡΡ ΠΎΠ±ΠΌΠ΅Π½ΠΎΠΌ ΡΠ½Π΅ΡΠ³ΠΈΠ΅ΠΉ ΠΌΠ΅ΠΆΠ΄Ρ ΠΏΠΎΡΠΎΠΊΠΎΠΌ Π³Π°Π·Π° ΠΈ ΠΊΠΎΠ»Π΅Π±Π»ΡΡΠΈΠΌΠΈΡΡ Π»ΠΎΠΏΠ°ΡΠΊΠ°ΠΌΠΈ ΠΈ ΡΠΎΡΡΠ°Π²Π»ΡΡΡ ΠΎΡΠ½ΠΎΠ²Ρ ΡΠΈΠ·ΠΈΡΠ΅ΡΠΊΠΎΠ³ΠΎ ΠΌΠ΅Ρ
Π°Π½ΠΈΠ·ΠΌΠ° ΡΠ°ΠΌΠΎΠ²ΠΎΠ·Π±ΡΠΆΠ΄Π°ΡΡΠΈΡ
ΡΡ ΠΊΠΎΠ»Π΅Π±Π°Π½ΠΈΠΉ, ΠΊΠΎΡΠΎΡΡΠ΅ ΠΌΠΎΠ³ΡΡ ΠΈΠ»ΠΈ Π·Π°ΡΡΡ
Π°ΡΡ (Π°ΡΡΠΎΠ΄Π΅ΠΌΠΏΡΠΈΡΠΎΠ²Π°Π½ΠΈΠ΅), ΠΈΠ»ΠΈ ΠΏΡΠΎΡΠ²Π»ΡΡΡΡΡ Π² ΡΡΡΠΎΠΉΡΠΈΠ²ΠΎΠΉ ΡΠΎΡΠΌΠ΅ Π°Π²ΡΠΎΠΊΠΎΠ»Π΅Π±Π°Π½ΠΈΠΉ, ΠΈΠ»ΠΈ Π² Π½Π΅ΡΡΡΠΎΠΉΡΠΈΠ²ΠΎΠΉ ΡΠΎΡΠΌΠ΅ ΡΠ»Π°ΡΡΠ΅ΡΠ°, ΠΊΠΎΡΠΎΡΡΠΉ ΠΌΠΎΠΆΠ΅Ρ ΠΏΡΠΈΠ²Π΅ΡΡΠΈ ΠΊ ΡΠ°Π·ΡΡΡΠ΅Π½ΠΈΡ ΠΊΠΎΠ½ΡΡΡΡΠΊΡΠΈΠΈ. ΠΠΎΡΡΠΎΠΌΡ Π°ΡΡΠΎΡΠΏΡΡΠ³ΠΎΠ΅ ΠΏΠΎΠ²Π΅Π΄Π΅Π½ΠΈΠ΅ Π»ΠΎΠΏΠ°ΡΠΎΠΊ ΠΏΡΠ΅Π΄ΡΡΠ°Π²Π»ΡΠ΅Ρ Π²Π°ΠΆΠ½ΡΡ ΠΏΡΠΎΠ±Π»Π΅ΠΌΡ Π½Π°Π΄Π΅ΠΆΠ½ΠΎΡΡΠΈ ΠΈ Π±Π΅Π·ΠΎΠΏΠ°ΡΠ½ΠΎΡΡΠΈ Π³Π°Π·ΠΎ- ΠΈ ΠΏΠ°ΡΠΎΡΡΡΠ±ΠΈΠ½Π½ΡΡ
Π΄Π²ΠΈΠ³Π°ΡΠ΅Π»Π΅ΠΉ Ρ Π²ΡΡΠΎΠΊΠΈΠΌΠΈ Π°ΡΡΠΎΠ΄ΠΈΠ½Π°ΠΌΠΈΡΠ΅ΡΠΊΠΈΠΌΠΈ ΠΏΠΎΠΊΠ°Π·Π°ΡΠ΅Π»ΡΠΌΠΈ ΠΈ ΡΠΎΠΎΡΠ²Π΅ΡΡΡΠ²Π΅Π½Π½ΠΎ Π²ΡΡΠΎΠΊΠΎ Π½Π°Π³ΡΡΠΆΠ΅Π½Π½ΡΠΌΠΈ Π»ΠΎΠΏΠ°ΡΠΊΠ°ΠΌΠΈ. ΠΠ΄Π½ΠΈΠΌ ΠΈΠ· ΠΏΠΎΠ΄Ρ
ΠΎΠ΄ΠΎΠ² ΠΊ ΠΏΠΎΠ²ΡΡΠ΅Π½ΠΈΡ ΡΡΡΠΎΠΉΡΠΈΠ²ΠΎΡΡΠΈ ΠΊΠΎΠ»Π΅Π±Π°Π½ΠΈΠΉ Π»ΠΎΠΏΠ°ΡΠΎΠΊ ΡΠ²Π»ΡΠ΅ΡΡΡ ΡΠ°ΡΡΡΡΠΎΠΉΠΊΠ° ΡΠΎΠ±ΡΡΠ²Π΅Π½Π½ΡΡ
ΡΠΎΡΠΌ, ΡΠ²ΡΠ·Π°Π½Π½Π°Ρ Ρ Π΄Π΅ΡΠΎΡΠΌΠ°ΡΠΈΠ΅ΠΉ Π΄ΠΈΡΠΊΠ°. ΠΡΠ΅Π΄ΡΡΠ°Π²Π»Π΅Π½ ΡΠΈΡΠ»Π΅Π½Π½ΡΠΉ Π°Π½Π°Π»ΠΈΠ· Π²Π»ΠΈΡΠ½ΠΈΡ Π΄Π΅ΡΠΎΡΠΌΠ°ΡΠΈΠΈ Π΄ΠΈΡΠΊΠ° Π½Π° Π°ΡΡΠΎΡΠΏΡΡΠ³ΠΈΠ΅ ΠΊΠΎΠ»Π΅Π±Π°Π½ΠΈΡ Π»ΠΎΠΏΠ°ΡΠΎΠΊ ΡΠ°Π±ΠΎΡΠ΅Π³ΠΎ ΠΊΠΎΠ»Π΅ΡΠ° ΡΡΡΠ±ΠΎΠΌΠ°ΡΠΈΠ½Ρ. ΠΠ΅ΡΠΎΡΠΌΠ°ΡΠΈΡ Π΄ΠΈΡΠΊΠ° Ρ
Π°ΡΠ°ΠΊΡΠ΅ΡΠΈΠ·ΡΠ΅ΡΡΡ ΠΊΠΎΠ»ΠΈΡΠ΅ΡΡΠ²ΠΎΠΌ ΡΠ·Π»ΠΎΠ²ΡΡ
Π΄ΠΈΠ°ΠΌΠ΅ΡΡΠΎΠ², ΡΡΠΎ ΠΎΠΏΡΠ΅Π΄Π΅Π»ΡΠ΅Ρ ΠΌΠ΅ΠΆΠ»ΠΎΠΏΠ°ΡΠΎΡΠ½ΡΠΉ ΡΠ³ΠΎΠ» ΡΠ΄Π²ΠΈΠ³Π° ΠΏΠΎ ΡΠ°Π·Π΅ ΠΊΠΎΠ»Π΅Π±Π°Π½ΠΈΠΉ ΡΠΎΡΠ΅Π΄Π½ΠΈΡ
Π»ΠΎΠΏΠ°ΡΠΎΠΊ (ΠΠΠ€Π£), ΠΊΠΎΡΠΎΡΡΠΉ Π²Π»ΠΈΡΠ΅Ρ Π½Π° Π½Π΅ΡΡΠ°ΡΠΈΠΎΠ½Π°ΡΠ½ΡΠ΅ Π°ΡΡΠΎΠ΄ΠΈΠ½Π°ΠΌΠΈΡΠ΅ΡΠΊΠΈΠ΅ Π½Π°Π³ΡΡΠ·ΠΊΠΈ ΠΈ Π°ΠΌΠΏΠ»ΠΈΡΡΠ΄Ρ ΠΊΠΎΠ»Π΅Π±Π°Π½ΠΈΠΉ Π»ΠΎΠΏΠ°ΡΠΎΠΊ. Π ΡΠ°Π±ΠΎΡΠ΅ ΠΏΠΎΠΊΠ°Π·Π°Π½ΠΎ, ΡΡΠΎ ΡΠΌΠ΅Π½ΡΡΠ΅Π½ΠΈΠ΅ ΠΌΠ΅ΠΆΠ»ΠΎΠΏΠ°ΡΠΎΡΠ½ΠΎΠ³ΠΎ ΡΠ³Π»Π° ΡΠ΄Π²ΠΈΠ³Π° ΠΏΠΎ ΡΠ°Π·Π΅ ΠΊΠΎΠ»Π΅Π±Π°Π½ΠΈΠΉ Π»ΠΎΠΏΠ°ΡΠΎΠΊ ΠΏΡΠΈΠ²ΠΎΠ΄ΠΈΡ ΠΊ ΠΏΠΎΠ²ΡΡΠ΅Π½ΠΈΡ Π°ΡΡΠΎΡΠΏΡΡΠ³ΠΎΠΉ ΡΡΡΠΎΠΉΡΠΈΠ²ΠΎΡΡΠΈ, Ρ. Π΅. ΠΊ ΡΠ½ΠΈΠΆΠ΅Π½ΠΈΡ Π°ΠΌΠΏΠ»ΠΈΡΡΠ΄ ΠΊΠΎΠ»Π΅Π±Π°Π½ΠΈΠΉ Π»ΠΎΠΏΠ°ΡΠΎΠΊ. ΠΡΠ΅Π΄Π»ΠΎΠΆΠ΅Π½Π½ΡΠΉ ΡΠΈΡΠ»Π΅Π½Π½ΡΠΉ ΠΌΠ΅ΡΠΎΠ΄ ΡΠ΅ΡΠ΅Π½ΠΈΡ ΡΠ²ΡΠ·Π°Π½Π½ΠΎΠΉ Π°ΡΡΠΎΡΠΏΡΡΠ³ΠΎΠΉ Π·Π°Π΄Π°ΡΠΈ Π² ΡΡΠ΅Ρ
ΠΌΠ΅ΡΠ½ΠΎΠΌ ΡΡΠ°Π½Π·Π²ΡΠΊΠΎΠ²ΠΎΠΌ ΠΏΠΎΡΠΎΠΊΠ΅ ΠΈΠ΄Π΅Π°Π»ΡΠ½ΠΎΠ³ΠΎ Π³Π°Π·Π° ΠΏΠΎΠ·Π²ΠΎΠ»ΡΠ΅Ρ ΠΏΡΠΎΠ³Π½ΠΎΠ·ΠΈΡΠΎΠ²Π°ΡΡ Π°ΡΡΠΎΡΠΏΡΡΠ³ΠΎΠ΅ ΠΏΠΎΠ²Π΅Π΄Π΅Π½ΠΈΠ΅ Π»ΠΎΠΏΠ°ΡΠΎΠΊ, Π²ΠΊΠ»ΡΡΠ°Ρ Π²ΡΠ½ΡΠΆΠ΄Π΅Π½Π½ΡΠ΅, ΡΠ°ΠΌΠΎΠ²ΠΎΠ·Π±ΡΠΆΠ΄Π°ΡΡΠΈΠ΅ΡΡ ΠΊΠΎΠ»Π΅Π±Π°Π½ΠΈΡ ΠΈ Π°Π²ΡΠΎΠΊΠΎΠ»Π΅Π±Π°Π½ΠΈΡ Ρ ΡΠ΅Π»ΡΡ ΠΏΠΎΠ²ΡΡΠ΅Π½ΠΈΡ ΡΠΊΠΎΠ½ΠΎΠΌΠΈΡΠ½ΠΎΡΡΠΈ ΠΈ Π½Π°Π΄Π΅ΠΆΠ½ΠΎΡΡΠΈ Π»ΠΎΠΏΠ°ΡΠΎΡΠ½ΡΡ
Π°ΠΏΠΏΠ°ΡΠ°ΡΠΎΠ² ΡΡΡΠ±ΠΎΠΌΠ°ΡΠΈΠ½.The unsteady phenomena caused by blades oscillations by action of forced forces are characterized with energy change between gas flow and oscillating blades and formulate the base of physical mechanism of self-excited oscillations that can or to attenuate (aerodamping), or to be displayed in stable form of autooscillations, or in unstable form of flutter, which can activate to the structure destruction. Therefore aeroelastic blades behaviour
represents the important problem of reliability and safety of gas and steam turbines with high aerodynamic indicators and high loaded blades. One of approaches to increase the stable blades oscillations is detuning of natural forms bound to disc deformation. There presented the numerical analysis of effect of disc deformation on aeroelastic blades oscillations of turbomachine blade row. The disc deformation is characterized by disc nodal diameters number that defines the interblade phase angle of blades oscillations shift (IBPA), and impacts on unsteady aerodynamic loads and blades oscillations amplitudes. In paper there shown that decrease of IBPA causes to increase of aeroelastic stability that is to reduction of blades oscillations amplitudes.The proposed numerical method of coupled aeroelastic problem solution for threedimensional transonic ideal gas flow allows to predict aeroelastic
behaviour of blades including the forced, self-excitation oscillations and autooscillations with purpose to increase the efficiency and reliability of turbomachines blades devices
Computational fluid dynamics analysis of 1 MW steam turbine inlet geometries
This paper analyses the influence of three different ring-type inlet duct geometries on the performance of a small 1 MW backpressure steam turbine. It examines the efficiency and pressure drop of seven turbine variants, including four spiral inlet geometries and three stages with a mass flow rate around 30 t/h. A one-pipe and two-pipe inlets are analysed from aerodynamical point of view, taking into account stator and rotor blades in three stages without the outlet. An outlet is added to the best variant. Also analysed is the occurrence of vortices in the inlets of the studied variants 1β7 as well as the efficiency, drop pressure, turbine power and mass flow. Finally, the best inlet for a 1 MW steam turbine is suggested
Π§ΠΠ‘ΠΠΠ¬ΠΠΠ ΠΠΠΠΠΠ ΠΠΠ ΠΠΠ Π£ΠΠΠΠ₯ ΠΠΠΠΠΠΠΠ¬ ΠΠΠΠΠ’ΠΠΠΠΠΠ ΠΠΠΠ¦Π― Π’Π£Π ΠΠΠΠΠ¨ΠΠΠ Π Π£Π ΠΠ₯Π£ΠΠΠΠΠ―Π ΠΠΠ€ΠΠ ΠΠΠ¦ΠΠ ΠΠΠ‘ΠΠ£
The unsteady phenomena caused by blades oscillations by action of forced forces are characterized with energy change between gas flow and oscillating blades and formulate the base of physical mechanism of self-excited oscillations that can or to attenuate (aerodamping), or to be displayed in stable form of autooscillations, or in unstable form of flutter, which can activate to the structure destruction. Therefore aeroelastic blades behaviour represents the important problem of reliability and safety of gas and steam turbines with high aerodynamic indicators and high loaded blades. One of approaches to increase the stable blades oscillations is detuning of natural forms bound to disc deformation. There presented the numerical analysis of effect of disc deformation on aeroelastic blades oscillations of turbomachine blade row. The disc deformation is characterized by disc nodal diameters number that defines the interblade phase angle of blades oscillations shift (IBPA), and impacts on unsteady aerodynamic loads and blades oscillations amplitudes. In paper there shown that decrease of IBPA causes to increase of aeroelastic stability that is to reduction of blades oscillations amplitudes. The proposed numerical method of coupled aeroelastic problem solution for threedimensional transonic ideal gas flow allows to predict aeroelastic behaviour of blades including the forced, self-excitation oscillations and autooscillations with purpose to increase the efficiency and reliability of turbomachines blades devices.ΠΠ΅ΡΡΠ°ΡΡΠΎΠ½Π°ΡΠ½Ρ ΡΠ²ΠΈΡΠ°, Π²ΠΈΠΊΠ»ΠΈΠΊΠ°Π½Ρ ΠΊΠΎΠ»ΠΈΠ²Π°Π½Π½ΡΠΌΠΈ Π»ΠΎΠΏΠ°ΡΠΎΠΊ ΠΏΡΠ΄ Π΄ΡΡΡ ΡΠΈΠ», ΡΠΎ ΠΎΠ±ΡΡΡΡΡΡ, Ρ
Π°ΡΠ°ΠΊΡΠ΅ΡΠΈΠ·ΡΡΡΡΡΡ ΠΎΠ±ΠΌΡΠ½ΠΎΠΌ Π΅Π½Π΅ΡΠ³ΡΡΡ ΠΌΡΠΆ ΠΏΠΎΡΠΎΠΊΠΎΠΌ Π³Π°Π·Ρ Ρ ΠΊΠΎΠ»ΠΈΠ²Π½ΠΈΠΌΠΈ Π»ΠΎΠΏΠ°ΡΠΊΠ°ΠΌΠΈ Ρ ΡΠΊΠ»Π°Π΄Π°ΡΡΡ ΠΎΡΠ½ΠΎΠ²Ρ ΡΡΠ·ΠΈΡΠ½ΠΎΠ³ΠΎ ΠΌΠ΅Ρ
Π°Π½ΡΠ·ΠΌΡ ΡΠ°ΠΌΠΎΠ·Π±ΡΠ΄Π½ΠΈΡ
ΠΊΠΎΠ»ΠΈΠ²Π°Π½Ρ, ΡΠΊΡ ΠΌΠΎΠΆΡΡΡ Π°Π±ΠΎ Π·Π°ΡΡΡ
Π°ΡΠΈ (Π°Π΅ΡΠΎΠ΄Π΅ΠΌΠΏΡΡΠ²Π°Π½Π½Ρ), Π°Π±ΠΎ ΠΏΡΠΎΡΠ²Π»ΡΡΠΈΡΡ Π² ΡΡΡΠΉΠΊΡΠΉ ΡΠΎΡΠΌΡ Π°Π²ΡΠΎΠΊΠΎΠ»ΠΈΠ²Π°Π½Ρ, Π°Π±ΠΎ Π² Π½Π΅ΡΡΡΠΉΠΊΡΠΉ ΡΠΎΡΠΌΡ ΡΠ»Π°ΡΠ΅ΡΠ°, ΡΠΊΠΈΠΉ ΠΌΠΎΠΆΠ΅ ΠΏΡΠΈΠ²Π΅ΡΡΠΈ Π΄ΠΎ ΡΡΠΉΠ½ΡΠ²Π°Π½Π½Ρ ΠΊΠΎΠ½ΡΡΡΡΠΊΡΡΡ. Π’ΠΎΠΌΡ Π°Π΅ΡΠΎΠΏΡΡΠΆΠ½Π° ΠΏΠΎΠ²Π΅Π΄ΡΠ½ΠΊΠ° Π»ΠΎΠΏΠ°ΡΠΎΠΊ ΡΠ²Π»ΡΡ Π²Π°ΠΆΠ»ΠΈΠ²Ρ ΠΏΡΠΎΠ±Π»Π΅ΠΌΡ Π½Π°Π΄ΡΠΉΠ½ΠΎΡΡΡ Ρ Π±Π΅Π·ΠΏΠ΅ΠΊΠΈ Π³Π°Π·ΠΎ- Ρ ΠΏΠ°ΡΠΎΡΡΡΠ±ΡΠ½Π½ΠΈΡ
Π΄Π²ΠΈΠ³ΡΠ½ΡΠ² Π· Π²ΠΈΡΠΎΠΊΠΈΠΌΠΈ Π°Π΅ΡΠΎΠ΄ΠΈΠ½Π°ΠΌΡΡΠ½ΠΈΠΌΠΈ ΠΏΠΎΠΊΠ°Π·Π½ΠΈΠΊΠ°ΠΌΠΈ Ρ Π²ΡΠ΄ΠΏΠΎΠ²ΡΠ΄Π½ΠΎ Π²ΠΈΡΠΎΠΊΠΎ Π½Π°Π²Π°Π½ΡΠ°ΠΆΠ΅Π½ΠΈΠΌΠΈ Π»ΠΎΠΏΠ°ΡΠΊΠ°ΠΌΠΈ. ΠΠ΄Π½ΠΈΠΌ Π· ΠΏΡΠ΄Ρ
ΠΎΠ΄ΡΠ² Π΄ΠΎ ΠΏΡΠ΄Π²ΠΈΡΠ΅Π½Π½Ρ ΡΡΡΠΉΠΊΠΎΡΡΡ ΠΊΠΎΠ»ΠΈΠ²Π°Π½Ρ Π»ΠΎΠΏΠ°ΡΠΎΠΊ Ρ ΡΠΎΠ·Π»Π°Π΄ Π²Π»Π°ΡΠ½ΠΈΡ
ΡΠΎΡΠΌ, ΠΏΠΎΠ²'ΡΠ·Π°Π½ΠΈΠΉ Π· Π΄Π΅ΡΠΎΡΠΌΠ°ΡΡΡΡ Π΄ΠΈΡΠΊΠ°. ΠΡΠ΅Π΄ΡΡΠ°Π²Π»Π΅Π½ΠΎ ΡΠΈΡΠ΅Π»ΡΠ½ΠΈΠΉ Π°Π½Π°Π»ΡΠ· Π²ΠΏΠ»ΠΈΠ²Ρ Π΄Π΅ΡΠΎΡΠΌΠ°ΡΡΡ Π΄ΠΈΡΠΊΠ° Π½Π° Π°Π΅ΡΠΎΠΏΡΡΠΆΠ½Ρ ΠΊΠΎΠ»ΠΈΠ²Π°Π½Π½Ρ Π»ΠΎΠΏΠ°ΡΠΎΠΊ ΡΠΎΠ±ΠΎΡΠΎΠ³ΠΎ ΠΊΠΎΠ»Π΅ΡΠ° ΡΡΡΠ±ΠΎΠΌΠ°ΡΠΈΠ½ΠΈ. ΠΠ΅ΡΠΎΡΠΌΠ°ΡΡΡ Π΄ΠΈΡΠΊΠ° Ρ
Π°ΡΠ°ΠΊΡΠ΅ΡΠΈΠ·ΡΡΡΡΡΡ ΠΊΡΠ»ΡΠΊΡΡΡΡ Π²ΡΠ·Π»ΠΎΠ²ΠΈΡ
Π΄ΡΠ°ΠΌΠ΅ΡΡΡΠ², ΡΠΎ Π²ΠΈΠ·Π½Π°ΡΠ°Ρ ΠΌΡΠΆΠ»ΠΎΠΏΠ°ΡΠΊΠΎΠ²ΠΈΠΉ ΠΊΡΡ Π·ΡΡΠ²Ρ ΠΏΠΎ ΡΠ°Π·Ρ ΠΊΠΎΠ»ΠΈΠ²Π°Π½Ρ ΡΡΡΡΠ΄Π½ΡΡ
Π»ΠΎΠΏΠ°ΡΠΎΠΊ (ΠΠΠ€Π), ΡΠΊΠΈΠΉ Π²ΠΏΠ»ΠΈΠ²Π°Ρ Π½Π° Π½Π΅ΡΡΠ°ΡΡΠΎΠ½Π°ΡΠ½Ρ Π°Π΅ΡΠΎΠ΄ΠΈΠ½Π°ΠΌΡΡΠ½Ρ Π½Π°Π²Π°Π½ΡΠ°ΠΆΠ΅Π½Π½Ρ Ρ Π°ΠΌΠΏΠ»ΡΡΡΠ΄ΠΈ ΠΊΠΎΠ»ΠΈΠ²Π°Π½Ρ Π»ΠΎΠΏΠ°ΡΠΎΠΊ. Π ΡΠΎΠ±ΠΎΡΡ ΠΏΠΎΠΊΠ°Π·Π°Π½ΠΎ, ΡΠΎ Π·ΠΌΠ΅Π½ΡΠ΅Π½Π½Ρ ΠΌΡΠΆΠ»ΠΎΠΏΠ°ΡΠΊΠΎΠ²ΠΎΠ³ΠΎ ΠΊΡΡΠ° Π·ΡΡΠ²Ρ ΠΏΠΎ ΡΠ°Π·Ρ ΠΊΠΎΠ»ΠΈΠ²Π°Π½Ρ Π»ΠΎΠΏΠ°ΡΠΎΠΊ ΠΏΡΠΈΠ·Π²ΠΎΠ΄ΠΈΡΡ Π΄ΠΎ ΠΏΡΠ΄Π²ΠΈΡΠ΅Π½Π½Ρ Π°Π΅ΡΠΎΠΏΡΡΠΆΠ½ΠΎΡ ΡΡΡΠΉΠΊΠΎΡΡΡ, ΡΠΎΠ±ΡΠΎ Π΄ΠΎ Π·Π½ΠΈΠΆΠ΅Π½Π½Ρ Π°ΠΌΠΏΠ»ΡΡΡΠ΄ ΠΊΠΎΠ»ΠΈΠ²Π°Π½Ρ Π»ΠΎΠΏΠ°ΡΠΎΠΊ. ΠΠ°ΠΏΡΠΎΠΏΠΎΠ½ΠΎΠ²Π°Π½ΠΈΠΉ ΡΠΈΡΠ΅Π»ΡΠ½ΠΈΠΉ ΠΌΠ΅ΡΠΎΠ΄ ΡΠΎΠ·Π²'ΡΠ·Π°Π½Π½Ρ Π·Π²'ΡΠ·Π°Π½ΠΎΡ Π°Π΅ΡΠΎΠΏΡΡΠΆΠ½ΠΎΡ Π·Π°Π΄Π°ΡΡ Π² ΡΡΠΈΠ²ΠΈΠΌΡΡΠ½ΠΎΠΌΡ ΡΡΠ°Π½Π·Π²ΡΠΊΠΎΠ²ΠΎΠΌΡ ΠΏΠΎΡΠΎΡΡ ΡΠ΄Π΅Π°Π»ΡΠ½ΠΎΠ³ΠΎ Π³Π°Π·Ρ Π΄ΠΎΠ·Π²ΠΎΠ»ΡΡ ΠΏΡΠΎΠ³Π½ΠΎΠ·ΡΠ²Π°ΡΠΈ Π°Π΅ΡΠΎΠΏΡΡΠΆΠ½Ρ ΠΏΠΎΠ²Π΅Π΄ΡΠ½ΠΊΡ Π»ΠΎΠΏΠ°ΡΠΎΠΊ, Π²ΠΊΠ»ΡΡΠ°ΡΡΠΈ Π²ΠΈΠΌΡΡΠ΅Π½Ρ, ΡΠ°ΠΌΠΎΠ·Π±ΡΠ΄Π½Ρ ΠΊΠΎΠ»ΠΈΠ²Π°Π½Π½Ρ Ρ Π°Π²ΡΠΎΠΊΠΎΠ»ΠΈΠ²Π°Π½Π½Ρ Π· ΠΌΠ΅ΡΠΎΡ ΠΏΡΠ΄Π²ΠΈΡΠ΅Π½Π½Ρ Π΅ΠΊΠΎΠ½ΠΎΠΌΡΡΠ½ΠΎΡΡΡ Ρ Π½Π°Π΄ΡΠΉΠ½ΠΎΡΡΡ Π»ΠΎΠΏΠ°ΡΠΎΠΊ Π°ΠΏΠ°ΡΠ°ΡΡΠ² ΡΡΡΠ±ΠΎΠΌΠ°ΡΠΈΠ½
Steam turbine stress control using NARX neural network
Considered here is concept of steam turbine
stress control, which is based on Nonlinear AutoRegressive
neural networks with eXogenous inputs. Using NARX
neural networks,whichwere trained based on experimentally
validated FE model allows to control stresses in protected
thickwalled steam turbine element with FE model
quality. Additionally NARX neural network, which were
trained base on FE model, includes: nonlinearity of steam
expansion in turbine steam path during transients, nonlinearity
of heat exchange inside the turbine during transients
and nonlinearity of material properties during transients.
In this article NARX neural networks stress controls
is shown as an example of HP rotor of 18K390 turbine.
HP part thermodynamic model as well as heat exchange
model in vicinity of HP rotor,whichwere used in FE model
of the HP rotor and the HP rotor FE model itself were validated
based on experimental data for real turbine transient
events. In such a way it is ensured that NARX neural
network behave as real HP rotor during steam turbine transient
events
Π§ΠΠ‘ΠΠΠΠΠ«Π ΠΠΠΠΠΠ Π’Π ΠΠ₯ΠΠΠ ΠΠΠΠ ΠΠΠ‘Π’ΠΠ¦ΠΠΠΠΠ ΠΠΠΠ ΠΠΠ’ΠΠΠ ΠΠΠΠΠΠ¬ΠΠΠΠ ΠΠΠΠ Π ΠΠΠ‘ΠΠΠΠΠΠ Π‘Π’Π£ΠΠΠΠ Π’Π£Π ΠΠΠΠΠ¨ΠΠΠ« Π‘ Π£Π§ΠΠ’ΠΠ ΠΠΠΠ‘ΠΠ‘ΠΠΠΠΠ’Π ΠΠ§ΠΠΠΠ ΠΠ«Π₯ΠΠΠΠΠΠΠ ΠΠΠ’Π Π£ΠΠΠ
A problem related to the forecast of the aeroelastic behavior and aeroelastic instability of blades (in particular self-oscillations, flutter, and resonance vibrations) becomes of great importance for the development of high-loaded compressor and vent rows and the last turbine stages whose long and flexible blades can be exposed to such phenomena. The solution of this problem requires the development of new models for the nonstationary three-dimensional flow, the use of contemporary numeric methods and the comparison of theoretical and experimental data. This scientific paper gives the data of numerical simulation of the 3-D flow of ideal gas passing through the last stage of turbine machine taking into account the flow nonuniformity caused by guide blades and nonuniform pressure distribution in the exhaust pipe branch and also nonstationary effects caused by blade vibrations. The numerical method is based on the solution of combined aeroelastic problem for the 3-D flow of ideal gas passing through the turbine stage and the nonaxisymmetric exhaust pipe branch including the annular diffuser. To solve the combined problem a partially integral method was used that includes integral equations of gas dynamics (Euler equations) and vibrating blade dynamics (modular approach) at each time step with the information exchange. The given method of the solution of combined aeroelastic problem allows us to predict the amplitude-frequency spectrum of blade vibrations in the three-dimensional flow of ideal gas including forced self-excited vibrations and self-vibrations to increase efficiency and reliability of the blade units of turbine machines.ΠΡΠ΅Π΄ΡΡΠ°Π²Π»Π΅Π½Ρ ΡΠ΅Π·ΡΠ»ΡΡΠ°ΡΡ ΡΠΈΡΠ»Π΅Π½Π½ΠΎΠ³ΠΎ ΠΌΠΎΠ΄Π΅Π»ΠΈΡΠΎΠ²Π°Π½ΠΈΡ ΡΡΠ΅Ρ
ΠΌΠ΅ΡΠ½ΠΎΠ³ΠΎ ΠΏΠΎΡΠΎΠΊΠ° ΠΈΠ΄Π΅Π°Π»ΡΠ½ΠΎΠ³ΠΎ Π³Π°Π·Π° ΡΠ΅ΡΠ΅Π· ΠΏΠΎΡΠ»Π΅Π΄Π½ΡΡ ΡΡΡΠΏΠ΅Π½Ρ ΡΡΡΠ±ΠΎΠΌΠ°ΡΠΈΠ½Ρ Ρ ΡΡΠ΅ΡΠΎΠΌ Π½Π΅ΡΠ°Π²Π½ΠΎΠΌΠ΅ΡΠ½ΠΎΡΡΠΈ ΠΏΠΎΡΠΎΠΊΠ°, Π²ΡΠ·Π²Π°Π½Π½ΠΎΠΉ Π½Π°ΠΏΡΠ°Π²Π»ΡΡΡΠΈΠΌΠΈ Π»ΠΎΠΏΠ°ΡΠΊΠ°ΠΌΠΈ, Π½Π΅ΠΎΡΠ΅ΡΠΈΠΌΠΌΠ΅ΡΡΠΈΡΠ½ΡΠΌ ΠΏΠ°ΡΡΡΠ±ΠΊΠΎΠΌ, ΠΈ Π½Π΅ΡΡΠ°ΡΠΈΠΎΠ½Π°ΡΠ½ΡΡ
ΡΡΡΠ΅ΠΊΡΠΎΠ², Π²ΡΠ·Π²Π°Π½Π½ΡΡ
ΠΊΠΎΠ»Π΅Π±Π°Π½ΠΈΡΠΌΠΈ Π»ΠΎΠΏΠ°ΡΠΎΠΊ. ΠΡΠ΅Π΄ΡΡΠ°Π²Π»Π΅Π½Π½ΡΠΉ ΠΌΠ΅ΡΠΎΠ΄ ΡΠ΅ΡΠ΅Π½ΠΈΡ ΡΠ²ΡΠ·Π°Π½Π½ΠΎΠΉ Π°ΡΡΠΎΡΠΏΡΡΠ³ΠΎΠΉ Π·Π°Π΄Π°ΡΠΈ ΠΏΠΎΠ·Π²ΠΎΠ»ΡΠ΅Ρ ΠΏΡΠΎΠ³Π½ΠΎΠ·ΠΈΡΠΎΠ²Π°ΡΡ Π°ΠΌΠΏΠ»ΠΈΡΡΠ΄Π½ΠΎ-ΡΠ°ΡΡΠΎΡΠ½ΡΠΉ ΡΠΏΠ΅ΠΊΡΡ ΠΊΠΎΠ»Π΅Π±Π°Π½ΠΈΠΉ Π»ΠΎΠΏΠ°ΡΠΎΠΊ, Π²ΠΊΠ»ΡΡΠ°Ρ Π²ΡΠ½ΡΠΆΠ΄Π΅Π½Π½ΡΠ΅, ΡΠ°ΠΌΠΎΠ²ΠΎΠ·Π±ΡΠΆΠ΄Π°ΡΡΠΈΠ΅ΡΡ ΠΊΠΎΠ»Π΅Π±Π°Π½ΠΈΡ ΠΈ Π°Π²ΡΠΎΠΊΠΎΠ»Π΅Π±Π°Π½ΠΈΡ Ρ ΡΠ΅Π»ΡΡ ΠΏΠΎΠ²ΡΡΠ΅Π½ΠΈΡ ΡΠΊΠΎΠ½ΠΎΠΌΠΈΡΠ½ΠΎΡΡΠΈ ΠΈ Π½Π°Π΄Π΅ΠΆΠ½ΠΎΡΡΠΈ Π»ΠΎΠΏΠ°ΡΠΎΡΠ½ΡΡ
Π°ΠΏΠΏΠ°ΡΠ°ΡΠΎΠ² ΡΡΡΠ±ΠΎΠΌΠ°ΡΠΈΠ½
Influence of inlet geometry on the efficiency of 1 MW steam turbine
The process of the design of the 1 MW steam turbine includes designing the stator and rotor blades, the steam
turbine inlet and exit, the casing and the rotor. A turbine that operates at rotation speeds other than 3000 rpm
requires a gearbox and generator with complex electronic software. This article analyses the efficiency of eight
turbine variants, including seven inlet geometries and three stages of stator as well as an eight variant with one of the
inlets, all three stages and an outlet.
This article analyses the efficiency of 8 turbine variants, including four spiral inlet geometries and tree stages in a
1 MW steam turbine. In the article, inlets and 1st stator blades of various geometries were analysed to obtain maximal
turbine efficiency. Changing the inlet spiral from one pipe to two pipes increased the turbine efficiency. The geometry
of the blades and turbine inlets and outlet was carried out using Design Modeller. The blade mesh was prepared in
TurboGrid and inlet in ANSYS Meshing
An influence of shroud design parameters on the static stresses of blade assemblies
In this study, the structural analysis of the blade assemblies was carried out using the finite element method to determine the influence of design parameters of shroud couplings on the static stresses of turbine rotor blades with zigzag and slant shroud couplings. An angle of inclination of the shroud contact surfaces with respect to the rotor rotation axis was selected as the design parameter. Based on the calculation results, it has been found that irrespective of the type of the shroud coupling, the values of the contact pressure and the stresses in the shroud increase with the angle of inclination of the contact surfaces. Also, for the slant shroud coupling, the stresses increase in the blade airfoil portion with the increase of angle of inclination of the contact surfaces, while for the zigzag shroud coupling the contact stresses decrease with the increase of this angle. It was concluded that the zigzag shroud coupling causes the increase in static stresses when compared to the slant one
Nonsynchronous Rotor Blade Vibrations in Last Stage of 380 MW LP Steam Turbine at Various Condenser Pressures
This paper presents an analysis of nonsynchronous rotor blade vibrations in the last stage of an LP steam turbine at various condenser pressures. The nonlinear least squares LevenbergβMarquardt method is used in a tip-timing analysis to determine nonsynchronous multimode rotor blade vibrations, which is a novelty. This is done with two sensors in the casing and a once-per-revolution sensor. The accuracy of the nonlinear least squares LevenbergβMarquardt multimode method is compared with the one-mode linear method. The algorithm is verified by comparing it with one-mode tip-timing methods for synchronous and nonsynchronous vibrations. The analysis shows that the rotor blades vibrate simultaneously with two modes in non-nominal conditions, which is also a novelty. The rotor frequencies are unchanged, although the blade vibration amplitudes vary, depending on the pressure in the condenser. Flutter does not appear in the last stage for the various condenser pressures and powers that were tested
Nonsynchronous Rotor Blade Vibrations in Last Stage of 380 MW LP Steam Turbine at Various Condenser Pressures
This paper presents an analysis of nonsynchronous rotor blade vibrations in the last stage of an LP steam turbine at various condenser pressures. The nonlinear least squares Levenberg–Marquardt method is used in a tip-timing analysis to determine nonsynchronous multimode rotor blade vibrations, which is a novelty. This is done with two sensors in the casing and a once-per-revolution sensor. The accuracy of the nonlinear least squares Levenberg–Marquardt multimode method is compared with the one-mode linear method. The algorithm is verified by comparing it with one-mode tip-timing methods for synchronous and nonsynchronous vibrations. The analysis shows that the rotor blades vibrate simultaneously with two modes in non-nominal conditions, which is also a novelty. The rotor frequencies are unchanged, although the blade vibration amplitudes vary, depending on the pressure in the condenser. Flutter does not appear in the last stage for the various condenser pressures and powers that were tested
Tip-timing analysis of last stage steam turbine mistuned bladed disc during run-down
This paper presents the experimental and numerical studies of last stage LP mistuned steam turbine bladed discs during run-down. The natural frequencies and mode shapes of the turbine bladed disc were calculated using an FE model. The influence of shaft was considered. The tip-timing method was used to find the mistuned bladed disc modes and frequencies. The numerical results were compared with experimental ones