The present invention relates to a gas turbine casing arrangement having a gas turbine casing element (10), a guide-vane ring with an outer ring (20), and a coated ring (30), which lies radially opposite a rotor grid (40) adjacent to the guide-vane ring, whereby an intermediate ring (50) by a downstream front face (51) engages behind an upstream stop (61; 61′) fixed in place on the casing element, and by an upstream front face (52) of a radial flange (53) of the intermediate ring engages behind a downstream stop (22) fixed in place on the outer ring, in order to secure the guide-vane ring axially at the gas turbine casing element in the direction of through-flow.

The present invention relates to a gas turbine casing arrangement having a gas turbine casing element (10), a guide-vane ring with an outer ring (20), and a coated ring (30), which lies radially opposite a rotor grid (40) adjacent to the guide-vane ring, whereby an intermediate ring (50) by a downstream front face (51) engages behind an upstream stop (61; 61′) fixed in place on the casing element, and by an upstream front face (52) of a radial flange (53) of the intermediate ring engages behind a downstream stop (22) fixed in place on the outer ring, in order to secure the guide-vane ring axially at the gas turbine casing element in the direction of through-flow.

Example apparatus, systems, and articles of manufacture to control deflection mismatch are disclosed herein. Further examples and combinations thereof include: A deflection limiter comprising an inner shroud segment to support a stator structure, the inner shroud segment including a first end face and a first outer upper portion, the first end face positioned radially inward and aft relative to the first outer upper portion, and an outer shroud segment to support the inner shroud segment, the outer shroud segment including a second end face and a second outer upper portion, the second end face positioned aft relative to the first end face and the second outer upper portion positioned aft relative to the first outer upper portion of the inner shroud segment, the second end face coupled to the first end face of the inner shroud segment and the second outer upper portion coupled to the first outer upper portion.

Example apparatus, systems, and articles of manufacture to control deflection mismatch are disclosed herein. Further examples and combinations thereof include: A deflection limiter comprising an inner shroud segment to support a stator structure, the inner shroud segment including a first end face and a first outer upper portion, the first end face positioned radially inward and aft relative to the first outer upper portion, and an outer shroud segment to support the inner shroud segment, the outer shroud segment including a second end face and a second outer upper portion, the second end face positioned aft relative to the first end face and the second outer upper portion positioned aft relative to the first outer upper portion of the inner shroud segment, the second end face coupled to the first end face of the inner shroud segment and the second outer upper portion coupled to the first outer upper portion.

A gas turbine engine is disclosed with a turbine section having at least one turbine rotor with a plurality of turbine blades, a plurality of blade tracks positioned circumferentially around the turbine blades, at least one dovetail shaped connecting member extending radially outward from each blade track, and a hanger connected to a structural member of the gas turbine engine and configured to releasably couple with the at least one dovetail shaped connecting member of a corresponding blade track.

A gas turbine engine is disclosed with a turbine section having at least one turbine rotor with a plurality of turbine blades, a plurality of blade tracks positioned circumferentially around the turbine blades, at least one dovetail shaped connecting member extending radially outward from each blade track, and a hanger connected to a structural member of the gas turbine engine and configured to releasably couple with the at least one dovetail shaped connecting member of a corresponding blade track.

An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.

The supercritical CO.sub.2 turbine in an embodiment includes: a rotary body; a stationary body housing the rotary body inside; and a turbine stage including a stator blade cascade in which a plurality of stator blades are supported inside the stationary body, and a rotor blade cascade in which a plurality of rotor blades are supported by the rotary body inside the stationary body, in which a supercritical CO.sub.2 working medium is introduced into the inside of the stationary body and flows via the turbine stage in an axial direction of the rotary body to thereby rotate the rotary body. Here, a thermal conductivity k1 and a specific heat c1 of a material constituting the rotary body and a thermal conductivity k2 and a specific heat c2 of a material constituting the stationary body satisfy a relationship represented by the following formula (A).

k1/c1≤k2/c2  formula (A)

The supercritical CO.sub.2 turbine in an embodiment includes: a rotary body; a stationary body housing the rotary body inside; and a turbine stage including a stator blade cascade in which a plurality of stator blades are supported inside the stationary body, and a rotor blade cascade in which a plurality of rotor blades are supported by the rotary body inside the stationary body, in which a supercritical CO.sub.2 working medium is introduced into the inside of the stationary body and flows via the turbine stage in an axial direction of the rotary body to thereby rotate the rotary body. Here, a thermal conductivity k1 and a specific heat c1 of a material constituting the rotary body and a thermal conductivity k2 and a specific heat c2 of a material constituting the stationary body satisfy a relationship represented by the following formula (A).

k1/c1≤k2/c2  formula (A)

A heatshield for a gas turbine engine includes a main body having a leading edge, a trailing edge, lateral edges, a first surface and a second surface, the first surface being exposed to a hot working gas in use passing through the gas turbine engine. The main body having an array of cooling channels for conveying a coolant flow, where each cooling channel of the array of cooling channels having a surface. At least one cooling channel of the array of cooling channels includes at least one flow disturbing feature extending from the surface and into the cooling channel.