Suction enabled post shutdown combustor cooling and ventilation

A gas turbine engine having a suction enabled post shutdown combustor cooling and ventilation system comprising:

• a gas turbine engine core flow path extending through a high pressure compressor, a combustor and a high pressure turbine, the high pressure turbine comprising high pressure turbine cooling air ports;
• a pump fluidly coupled with a suction line, wherein the suction line is fluidly coupled with bleed ports;
• a bleed port line fluidly coupled with the suction line proximate the bleed ports and upstream of the pump;
• a pump suction valve positioned in the suction line upstream of the pump;
• a bleed valve positioned in the bleed port line upstream of the pump suction valve;
• a pump discharge line fluidly coupled with the pump,
• an outlet fluidly coupled with the pump discharge line, the outlet is fluidly coupled with and discharges into a fan bypass duct;
• a core compartment supply line fluidly coupled with the high pressure turbine cooling air ports, the core compartment supply line comprising a core compartment inlet located within a core compartment and fluidly coupled with the core compartment, the core compartment supply line comprising a core compartment supply valve located in the core compartment supply line upstream of the high pressure turbine cooling air ports;
• a turbine cooling air supply line fluidly coupled to the core compartment supply line and the high pressure turbine cooling air ports, the turbine cooling air supply line comprising a turbine cooling air valve;
• and
• the gas turbine engine core flow path fluidly coupled with the bleed ports and the high pressure turbine cooling air ports.

A process for post shutdown combustor cooling and ventilation in a gas turbine engine having a suction enabled post shutdown system comprising:

• a gas turbine engine core flow path extending through a high pressure compressor, a combustor and a high pressure turbine, the high pressure turbine comprising high pressure turbine cooling air ports;
• fluidly coupling a pump with a suction line;
• fluidly coupling the suction line with bleed ports;
• fluidly coupling a bleed port line with the suction line proximate the bleed ports and upstream of the pump;
• positioning a pump suction valve in the suction line upstream of the pump;
• positioning a bleed valve in the bleed port line upstream of the pump suction valve;
• fluidly coupling a pump discharge line with the pump,
• fluidly coupling an outlet with the pump discharge line, the outlet is fluidly coupled with and discharges into a fan bypass duct;
• fluidly coupling a core compartment supply line with the high pressure turbine cooling air ports, the core compartment supply line comprising a core compartment inlet located within a core compartment;
• and fluidly coupling the core compartment inlet with the core compartment, the core compartment supply line comprising a core compartment supply valve located in the core compartment supply line upstream of the high pressure turbine cooling air ports;
• fluidly coupling a turbine cooling air supply line to the core compartment supply line and the high pressure turbine cooling air ports, the turbine cooling air supply line comprising a turbine cooling air valve;
• and
• fluidly coupling the gas turbine engine core flow path with the bleed ports and the high pressure turbine cooling air ports.