DEVICE TO REGULATE AIR BYPASSING FROM COMPRESSOR OR AIRCRAFT GAS-TURBINE ENGINE Russian patent published in 2003 - IPC

FIELD: aircraft engines. SUBSTANCE: invention relates to devices providing preset thrust and preservation of gas-dynamic stability margins of aircraft gas-turbine engine at possible failures. Invention is aimed at provision of stable operation of gas-turbine engine and preset thrust at takeoff regime in case of failures owing to improved accuracy and reliability of control under aircraft takeoff conditions: takeoff running, lift off, climbing with transition of high- lift devices of aircraft from takeoff into flight configuration. The problem is solved by proposed design owing to well-timed closing of air bypass valves in succession providing required margins of gas-dynamic stability and displacement of operating conditions line to lower gas temperatures, thus providing optimum calorific intensity of engine. In device for regulating air bypassing from compressor of aircraft gas-turbine engine including engine inlet temperature pickup and compressor rotor speed pickup and series connected first arithmetic unit and first comparator, aircraft chassis wheel rotation pickup, series- connected second arithmetic unit and second comparator and first and second group air bypass valves actuating unit and air bypass valves of first and second groups, according to invention, device includes additional engine control handle position pickup aircraft high-lift device position pickup, aircraft parking brake pickup, comparator, AND and OR logic gates. Output of additional pickups are connected to additional comparator, output of first comparator is connected to first input of first OR logic gate and output of additional comparator is connected to second input of OR logic gate. Output of OR logic gate is connected to input of actuating unit of air bypass valve of first group whose output is connected simultaneously with air bypass valve of first group and with first input of AND logic gate. Output of second comparator is connected with second input of AND logic gate , and its output is connected with input of actuating unit of air bypass valve of second group connected with air bypass valve of second group. Moreover, basing on results of flight trials, on airfields in tropic countries, stability margin for improving thermodynamic parameters of engine has been revealed, namely, possibility of correction of nthrvb

value depending on T_in. For this purpose, proposed device is furnished additionally with correction unit whose input is connected with output of engine inlet air temperature pickup, and output is connected with second input of first comparator. EFFECT: provision of stable operation of aircraft gas-turbine engine. 2 cl, 3 dwg