Ceramic vane ring-strut-ring attachment configuration
A gas turbine engine includes a turbine section that has inner and outer diameter full hoop ceramic support rings that define an annulus there between and ceramic vane arc segments disposed in the annulus. Each segment has radially outer and inner platforms and an airfoil section. The radially outer platform includes an outer platform flange. The radially outer full hoop ceramic support ring axially constrains each of the ceramic vane arc segments via the outer platform flanges, and the radially outer diameter full hoop ceramic support ring radially constrains each of the ceramic vane arc segments at a location adjacent an axially-facing trailing side of the radially outer platform. The radially inner diameter full hoop ceramic support ring radially constrains each of the ceramic vane arc segments at a location adjacent the axially-facing leading side of the radially inner platform.
1 . A gas turbine engine comprising:
a turbine section disposed about an engine axis, the turbine section including
inner and outer diameter full hoop ceramic support rings that define an annulus radially there between and ceramic vane arc segments disposed in the annulus, each of the ceramic vane arc segments including
radially outer and inner platforms and an airfoil section there between,
each of the radially outer and inner platforms including axially-facing leading and trailing sides, first and second radial sides, and first and second circumferential sides,
the radially outer platform including an outer platform flange extending from the second radial side adjacent the axially-facing leading side, the outer platform flange being elongated in a circumferential direction,
the radially outer full hoop ceramic support ring axially constraining each of the ceramic vane arc segments via the outer platform flanges, and the radially outer diameter full hoop ceramic support ring radially constraining each of the ceramic vane arc segments at a first location adjacent the axially-facing trailing side of the radially outer platform, and
the radially inner diameter full hoop ceramic support ring radially constraining each of the ceramic vane arc segments at a second location adjacent the axially-facing leading side of the radially inner platform.
2 . The gas turbine engine as recited in claim 1 , wherein the radially inner platform includes an inner platform flange that extends from the second radial side adjacent the axially-facing trailing side, and the inner platform flange is elongated in the circumferential direction.
3 . The gas turbine engine as recited in claim 2 , wherein the inner platform flange is axially trapped between the radially inner full hoop ceramic support ring and a radially inner static support.
4 . The gas turbine engine as recited in claim 2 , wherein the inner platform flange includes a branch that constrains circumferential movement of the radially inner full hoop support ring.
5 . The gas turbine engine as recited in claim 1 , wherein the radially outer platform includes a first load pad through which the radially outer diameter full hoop ceramic support ring radially constrains each ceramic vane arc segment, and the radially inner platform includes a second load pad through which the radially inner diameter full hoop ceramic support ring radially constrains each ceramic vane arc segment.
6 . The gas turbine engine as recited in claim 5 , wherein the first load pad and the second load pad are circumferentially-elongated bands.
7 . The gas turbine engine as recited in claim 1 , further comprising a radially outer static support that has an anti-rotation tab that constrains circumferential movement of each of the ceramic vane arc segments via the outer platform flanges and of the radially outer full hoop ceramic support ring.
8 . The gas turbine engine as recited in claim 1 , wherein the ceramic vane arc segments, the radially outer full hoop support ring, and the radially inner full hoop support ring are ceramic matrix composite.
9 . The gas turbine engine as recited in claim 1 , wherein each of the ceramic vane arc segments is a single piece structure including the outer platform flange and formed of a ceramic matrix composite that has fiber plies that are continuous from the radially outer platform, through the airfoil section, and into the radially inner platform.
10 . The gas turbine engine as recited in claim 9 , wherein the radially outer platform contacts the radially outer diameter full hoop ceramic support ring at the first location, and the radially inner platform contacts the radially inner diameter full hoop ceramic support ring at the second location.
11 . The gas turbine engine as recited in claim 1 , wherein the airfoil section has suction and pressure side, and when aerodynamic loads are exerted on the ceramic vane arc segments, the radially outer diameter full hoop ceramic support ring radially constrains each of the ceramic vane arc segments at the first location adjacent the axially-facing trailing side of the radially outer platform on the suction side of the radially outer platform and the radially inner diameter full hoop ceramic support ring radially constrains each of the ceramic vane arc segments at the second location adjacent the axially-facing leading side of the radially inner platform on the pressure side of the radially inner platform.