GAS TURBINE ENGINE SHUTDOWN TEMPERATURE CONTROL SYSTEM WITH INJECTION NOZZLE FOR GAS TURBINE ENGINE Russian patent published in 2018 - IPC F01D25/26 

FIELD: motors and pumps.

SUBSTANCE: invention relates to turbine engines, and more particularly to systems providing start-up from an unheated state of gas turbine engines without the risk of collision of a turbine blade with radially outer sealing surfaces. Gas turbine engine shutdown temperature control system (10) is configured to limit the creation of temperature gradients in outer casing (12) surrounding turbine blade assembly (14) while gas turbine engine (16) is turned off. By reducing the temperature gradients caused by the buoyancy of the hot air in cavities (18) of the middle region in outer casing (12), the arcuate and concave bending of outer casing (12) is prevented. Thus, the possibility of abrasion of the tip of the blade and the possible damage to the blade during the restart of gas turbine engine (16) from the non-heated state are reduced. Gas turbine engine shutdown temperature control system (10) can operate during the shutdown process, when rotor (26) is still driven by the combustion gases, or during the operation of the pivoting system after the gas turbine engine has been turned off, or during both, to ensure that outer casing (12) is evenly cooled downward.

EFFECT: gas turbine engine system shutdown temperature control system with an injection nozzle for a gas turbine engine is proposed.

6 cl, 8 dwg