Brian Kenneth Corsetti

Bio: Brian Kenneth Corsetti is an academic researcher from General Electric. The author has contributed to research in topics: Fillet (mechanics) & Shroud. The author has an hindex of 4, co-authored 11 publications receiving 193 citations.

Mounting apparatus for low-ductility turbine shroud

Abstract: A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member (14); (b) a turbine shroud (12) disposed in the support member (14), the shroud (12) being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring (32) mounted between the support member (14) and the shroud (12) and arranged to resiliently urge the shroud (12) to a concentric position within the support member (14).

Continuous ring composite turbine shroud

Abstract: A composite annular shroud (42) supported by a support assembly (46) including at least two single piece full 360 degree rings (50, 52, 54 or 130) and at least partially disposed within an innermost one of the rings. The shroud (42) is biased against and in sealing engagement with an inner flange (84) of the innermost ring. A three ring assembly includes the inner ring (50) disposed radially inwardly of a middle ring (52) disposed radially inwardly of an outer ring (54) and the shroud (42) at least partially disposed within the inner ring (50). At least three clocking pins (74) extend radially inwardly from the middle ring (52) through slots (76) in the inner ring (50) into notches (78) in the shroud (42). The middle ring (52) may be an aft end (70) of a support ring (68) fixedly connected to an engine backbone (58). Mounting pins (104) may be press fitted into pin holes (106) in the middle ring (52) and extend radially outwardly from the middle ring (52) through radial holes (107) in the outer ring (54).

Turbine engine with an airfoil having a tip shelf outlet

Abstract: An airfoil for a gas turbine engine includes a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. A tip shelf can be defined in the pressure or suction sidewalls. A film hole can extend to the tip shelf, such that the film hole can be shaped to direct a flow of cooling fluid to the film hole to improve film cooling at the tip shelf.

Fillet optimization for turbine airfoil

Abstract: A blade for a gas turbine engine comprises an airfoil having a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. The corners comprise fillets to define a thickness being greater than the thickness for the pressure, suction, or tip walls. A film hole can extend through the fillet, such that the length of the film hole at the fillet can be increased to define an increased length-to-diameter ratio for the film hole to improve film cooling through the film hole.

Gas turbine engine with fillet film holes

Abstract: An airfoil for a gas turbine engine can have an exterior wall and an interior wall, with each wall having a thickness. The walls can intersect to define a corner at the intersection. A cooling passage can be defined by the walls at or near the corner to provide fluid communication between the interior and exterior of the airfoil. A film hole can be disposed in the walls and can have a length and diameter to define a ratio of length to diameter, L/D. An arcuate fillet can be located in the corner to define an effective radius for the fillet. The effective radius can be at least 1.5 times larger than the thicknesses of the walls to provide for an increased length to diameter ratio for the film hole.

Mounting apparatus for low-ductility turbine shroud

Abstract: A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member (14); (b) a turbine shroud (12) disposed in the support member (14), the shroud (12) being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring (32) mounted between the support member (14) and the shroud (12) and arranged to resiliently urge the shroud (12) to a concentric position within the support member (14).

Turbine ring assembly

Abstract: A turbine ring assembly includes a ring support structure and a plurality of ring sectors, each including a single piece of ceramic matrix composite material. Each ring sector includes a first portion forming an annular base with an inside face defining an inside face of the turbine ring and an outside face from which there extends two tab-forming portions including ends that are engaged in housings in the ring support structure. The ring sectors present a section that is substantially π-shaped and the ends of the tabs are held without radial clearance by the ring support structure. The tabs can have a free length in meridian section that is not less than three times their mean width.

Turbine shroud sealing apparatus

Abstract: A turbine shroud sealing apparatus for a gas turbine engine includes: (a) an arcuate shroud segment comprising a low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces of the segment; and (b) a first seal assembly received in at least one slot formed in the first end face, the first seal assembly comprising one or more spline seals which protrude from the first end face and which are arranged to define a continuous sealing surface around the perimeter of the first end face

Continuous ring composite turbine shroud

Abstract: A composite annular shroud (42) supported by a support assembly (46) including at least two single piece full 360 degree rings (50, 52, 54 or 130) and at least partially disposed within an innermost one of the rings. The shroud (42) is biased against and in sealing engagement with an inner flange (84) of the innermost ring. A three ring assembly includes the inner ring (50) disposed radially inwardly of a middle ring (52) disposed radially inwardly of an outer ring (54) and the shroud (42) at least partially disposed within the inner ring (50). At least three clocking pins (74) extend radially inwardly from the middle ring (52) through slots (76) in the inner ring (50) into notches (78) in the shroud (42). The middle ring (52) may be an aft end (70) of a support ring (68) fixedly connected to an engine backbone (58). Mounting pins (104) may be press fitted into pin holes (106) in the middle ring (52) and extend radially outwardly from the middle ring (52) through radial holes (107) in the outer ring (54).

Shroud hanger assembly

Abstract: A shroud hanger assembly (30) or shroud assembly (30) is provided for a gas turbine engine wherein a hanger (32) includes a radially depending and axially extending arm. The arm (45) or retainer (60) engages a pocket (56) formed in a shroud (50) so as to retain the shroud (50) in a desired position relative to the hanger (32). An aft retaining structure is provided on the hanger (32) and provides a seat for a seal structure which biases the retainer (60) so that the arm (45) of the hanger (32) maintains engagement in the shroud pocket (56). A baffle (52) may be utilized at the hanger (32) to cool at least some portion of the shroud (50).