Aircraft engine accessory heat insulation cabin temperature control method

• Main Authors: LIU TAIQIU, LI YUNDAN, LI XIN, LIU GUOCHAO, ZHOU JIANJUN, YAN JIANKUN, PAN GUANGYAN, ZHANG CHUNLEI
• Format: Patent
• Language: Chinese; English
• Published: 22.12.2023
• Subjects: AIR INTAKES FOR JET-PROPULSION PLANTS; BLASTING; COMBUSTION ENGINES; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS; GAS-TURBINE PLANTS; HEATING; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS; LIGHTING; MECHANICAL ENGINEERING; WEAPONS

The invention belongs to the field of aero-engine temperature control, and relates to an aircraft engine accessory heat insulation cabin temperature control method, which comprises the following steps: arranging a heat insulation cabin on the outer side of an engine cabin, collecting temperature information in the heat insulation cabin through a signal collector, setting a working temperature limit value, and adjusting inlet airflow through a flow valve. Controlling a flow valve and a temperature control sensor to collect flow and temperature data in the heat insulation cabin in real time, judging whether the flow and temperature data exceed a working temperature limit value or not, and if yes, giving a temperature over-limit alarm; if not, the temperature control sensor is controlled to work normally; the real-time temperature control information of the engine is used as the boundary of temperature adjustment, and the bleed air flow is adjusted to achieve the temperature control target. Compared with a tradi