AIRCRAFT GAS TURBINE POWER PLANT Russian patent published in 2020 - IPC F01D25/08 

FIELD: engine building.

SUBSTANCE: invention relates to aircraft engine construction, in particular to small-sized gas turbine engines of aircraft. Gas-turbine power plant of aircraft comprises located in housing air intake channel, having hollow central fairing with inner shell, hollow posts with outlet holes and anti-icing device, multistage compressor with low-pressure cavity, turboengine with rotor impellers installed on output shaft, and above-rotor device with cooling chamber and cooling air supply channel, planetary reduction gear with switching mechanism connected to power plant control system, and starter-generator arranged inside central fairing and made in form of reversible electric machine with stator fixed on housing, rotor connected via planetary gearbox to engine output shaft, and cooling cavity with cooling air outlet channel, in which main controlled switch is installed, and pipeline communicated with low-pressure cavity of multi-stage compressor. Anti-icing device is made in form of air cavity formed between shell and central fairing, communicated with internal cavities of posts and connected to the first output of the main controlled switch, which is interconnected by the inlet with the cooling air discharge channel from the cooling cavity of the reversible electrical machine and connected to the power plant control system by the drive. Air intake channel is equipped with air collector communicated with hollow posts outlets. In cooling air supply channel to cooling chamber of above-rotor device additional controlled switch is installed, to one of the inputs of which the second output of the main controlled switch is connected, and to the other input through the additionally installed check valve – collector outlet. Drive of the additional controlled switch is connected to the control system of the power plant.

EFFECT: technical result of invention is increase of gas turbine power plant efficiency on cruise modes of aircraft flight, as well as reliability of power plant operation at maximum forced modes of turbo-engine operation.

1 cl, 3 dwg