US 12,421,870 B1
Pin mounted ceramic matrix composite heat shields with impingement cooling
Clark J. Snyder, Indianapolis, IN (US); Aaron D. Sippel, Indianapolis, IN (US); David J. Thomas, Indianapolis, IN (US); and Ted J. Freeman, Indianapolis, IN (US)
Assigned to Rolls-Royce Corporation, Indianapolis, IN (US)
Filed by Rolls-Royce Corporation, Indianapolis, IN (US)
Filed on Apr. 30, 2024, as Appl. No. 18/651,642.
Int. Cl. F01D 11/08 (2006.01); F01D 25/12 (2006.01); F01D 25/24 (2006.01)
CPC F01D 25/12 (2013.01) [F01D 25/243 (2013.01); F05D 2230/64 (2013.01); F05D 2260/232 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A turbine shroud assembly for use with a gas turbine engine, the turbine shroud assembly comprising
a blade track segment made of ceramic matrix composite materials having a shroud wall that extends circumferentially partway around an axis and an attachment flange that extends radially outward from the shroud wall away from the axis,
a pin that extends parallel to the axis into a metallic support structure and through an aperture in the attachment flange of the blade track segment so as to couple the blade track segment to the metallic support structure, and
a cooling passageway formed in the metallic support structure, the cooling passageway shaped to direct cooling air onto a preselected cooling area of the attachment flange included in the blade track segment, the preselected cooling area located radially between the shroud wall and the pin as well as being circumferentially aligned with the pin so that heat absorbed by the shroud wall during use of the turbine shroud assembly is dissipated by the cooling air directed onto the preselected cooling area before being conducted to the pin so as to manage pin-deformation and pin-life, an inlet of the cooling passageway offset from an outlet of the cooling passageway in a radial direction and in at least one of an axial direction relative to the axis or a circumferential direction relative to the axis,
wherein the metallic support structure includes a cooling air plenum, the cooling passageway in fluid communication with the cooling air plenum to conduct the cooling air through a wall of the metallic support structure to the preselected cooling area,
wherein the attachment flange is a first attachment flange, the blade track segment further comprising a second attachment flange that extends radially outward from the shroud wall, the second attachment flange spaced apart axially from the first attachment flange, and
wherein the metallic support structure includes a first intermediate support wall that extends radially inward from an outer wall of the metallic support structure axially aft of the first attachment flange and a second intermediate support wall that extends radially inward from the outer wall of the metallic support structure axially forward of the second attachment flange and spaced apart axially from the first intermediate support wall to define a chamber.