Gas turbine engine turbine nozzle bifurcated impingement baffle

A bifurcated impingement baffle comprising:

• axially forward and aft chambers with a gap therebetween,
• impingement holes through forward and aft baffle walls of the forward and aft chambers respectively,
• a plenum chamber in fluid flow communication with the forward and aft chambers,
• a single cooling air inlet to the plenum chamber,
• a sealing plate mounted between and sealed to the plenum chamber enclosure and the forward and aft chambers,
• the sealing plate having forward and aft inlet apertures disposed between the plenum chamber and the forward and aft chambers respectively,
• forward and aft end plates capping radially inner ends of the forward and aft chambers, and
• an outlet aperture in the forward end plate and an interstage seal cavity feed tube disposed through the outlet aperture.

A turbine nozzle segment comprising:

• at least one hollow airfoil extending radially between radially outer and inner band segments,
• the airfoil located between circumferentially spaced apart pressure and suction side edges of the radially outer and inner band segments,
• the airfoil having an airfoil wall with pressure and suction sides extending axially between leading and trailing edges of the airfoil,
• the airfoil wall surrounding a bifurcated cavity,
• a bifurcating rib extending through the bifurcated cavity and between the pressure and suction sides of the airfoil wall dividing the bifurcated cavity into forward and aft cavities,
• a bifurcated impingement baffle including axially forward and aft chambers with a gap therebetween,
• impingement holes through forward and aft baffle walls of the forward and aft chambers respectively,
• a plenum chamber in fluid flow communication with the forward and aft chambers, and
• a plenum chamber enclosure enclosing the plenum chamber and attached to the forward and aft chambers, and
• the forward and aft chambers disposed in the forward and aft cavities respectively.

A turbine nozzle segment comprising:

• at least one hollow airfoil extending radially between radially outer and inner band segments,
• the airfoil located between circumferentially spaced apart pressure and suction side edges of the radially outer and inner band segments,
• the airfoil having an airfoil wall with pressure and suction sides extending axially between leading and trailing edges of the airfoil,
• the airfoil wall surrounding a bifurcated cavity,
• a bifurcating rib extending through the bifurcated cavity and between the pressure and suction sides of the airfoil wall dividing the bifurcated cavity into forward and aft cavities,
• a bifurcated impingement baffle including axially forward and aft chambers with a gap therebetween,
• impingement holes through forward and aft baffle walls of the forward and aft chambers respectively,
• a plenum chamber in fluid flow communication with the forward and aft chambers,
• the forward and aft chambers disposed in the forward and aft cavities respectively,
• a single cooling air inlet to the plenum chamber,
• a plenum chamber enclosure enclosing the plenum chamber,
• a sealing plate mounted between and sealed to the plenum chamber enclosure and the forward and aft chambers,
• the sealing elate having forward and aft inlet apertures disposed between the plenum chamber and the forward and aft chambers respectively,
• forward and aft end plates capping radially inner ends of the forward and aft chambers, and
• an outlet aperture in the forward end plate and an interstage seal cavity feed tube disposed through the outlet aperture.

A turbine nozzle segment comprising:

• a single hollow airfoil extending radially between radially outer and inner band segments,
• the airfoil located between circumferentially spaced apart pressure and suction side edges of the radially outer and inner band segments,
• the airfoil having an airfoil wall with pressure and suction sides extending axially between leading and trailing edges of the airfoil,
• the airfoil wall surrounding a bifurcated cavity,
• a bifurcating rib extending through the bifurcated cavity and between the pressure and suction sides of the airfoil wall dividing the bifurcated cavity into forward and aft cavities,
• a bifurcated impingement baffle including axially forward and aft chambers with a gap therebetween,
• impingement holes through forward and aft baffle walls of the forward and aft chambers respectively,
• a plenum chamber in fluid flow communication with the forward and aft chambers, and
• a plenum chamber enclosure enclosing the plenum chamber and attached to the forward and aft chambers, and
• the forward and aft chambers disposed in the forward and aft cavities respectively.

A turbine nozzle segment comprising:

• a single hollow airfoil extending radially between radially outer and inner band segments,
• the airfoil located between circumferentially spaced apart pressure and suction side edges of the radially outer and inner band segments,
• the airfoil having an airfoil wall with pressure and suction sides extending axially between leading and trailing edges of the airfoil,
• the airfoil wall surrounding a bifurcated cavity,
• a bifurcating rib extending through the bifurcated cavity and between the pressure and suction sides of the airfoil wall dividing the bifurcated cavity into forward and aft cavities,
• a bifurcated impingement baffle including axially forward and aft chambers with a gap therebetween,
• impingement holes through forward and aft baffle walls of the forward and aft chambers respectively,
• a plenum chamber in fluid flow communication with the forward and aft chambers,
• the forward and aft chambers disposed in the forward and aft cavities respectively,
• a single cooling air inlet to the plenum chamber,
• at least one crossover hole,
• forward and aft end plates capping radially inner ends of the forward and aft chambers, and
• an outlet aperture in the forward end plate and an interstage seal cavity feed tube disposed through the outlet aperture.

A bifurcated impingement baffle comprising:

• axially forward and aft chambers with a gap therebetween,
• impingement holes through forward and aft baffle walls of the forward and aft chambers respectively,
• a plenum chamber in fluid flow communication with the forward and aft chambers,
• a single cooling air inlet to the plenum chamber,
• a sealing plate mounted between and sealed to the plenum chamber enclosure and the forward and aft chambers,
• the sealing plate having forward and aft inlet apertures disposed between the plenum chamber and the forward and aft chambers respectively,
• forward and aft end plates capping radially inner ends of the forward and aft chambers, and
• a plurality of crossover holes through the bifurcating rib.