A turbine wheel assembly adapted for use in a gas turbine engine is disclosed. The turbine wheel assembly includes components optionally made from ceramic matrix composite such as turbine blades and/or heat shields.

Turbine wheel with circumferentially-installed inter-blade heat shields

The shield member (30) is disposed over a gap between platform parts (20) of adjoining turbine rotor blades (10), is formed from a ceramic-based composite material, and shields the gap between the platform parts (20).

Shield member and jet engine using the same

FIELD: engines and pumps.SUBSTANCE: invention relates to the jet engine shielding elements. Shielding element (30) is located on above of the gaps between the turbine rotor adjacent blades (10) flange (20) sections and is made of a composite material with a ceramic matrix with possibility of the gap between the flange (20) sections shielding due to coming into contact along the flange sections bodies internal surfaces. From the airfoil input edge the shielding element section is made elongated and includes a second shielding surface located between the turbine rotor adjacent blades tail portions. Each of the flange sections includes a rear skirt, made on the flange section corresponding body output edge side. First contact areas are configured to come into contact with the turbine rotor adjacent blades tail sections side surfaces and with the rear skirts holding sections. Second contact areas are configured to come into contact with the turbine rotor adjacent blades tail sections side surfaces.EFFECT: technical result is the shielding of gaps between the turbine rotor adjacent blades flange sections.4 cl, 21 dwg

Shielding element and jet engine, in which such element is used

A seal structure for a gas turbine rotor blade wherein a shank (12) has a side surface (12a), a side surface (12b), and a bottom surface (12c) that is positioned farther inward in the radial direction than a fin (13). The side surface (12a) has a recess (17) in which a wedge seal member (20) is accommodated in a movable manner, and a slot (40) that is open on the bottom surface (12c) as an insertion opening (42) for a spline seal member (30). The side surface (12b) has a slot (43) that is provided at a position corresponding to the slot (40), and that is open on the bottom surface (12c) as the insertion opening (42) for the spline seal member (30). The recess (17) has a slanted surface (17a) that extends in a straight line so as to separate from the side surface (12a) in the direction radially inward from the side surface (12a). The wedge seal member (20) has: a wedge portion (21), which includes a wedge surface (21a) that faces the slanted surface (17a) and a wedge surface (21b) that faces the side surface (12b) of the adjacent rotor blade, and forms the apex of the wedge together with the wedge surface (21a); and a weight portion (22), which is formed integrally with the wedge portion (21), and is positioned inside the recess (17), farther inward in the radial direction than the wedge portion (21).

Ogawa Tomotake

Papers

Shield member and jet engine using the same

Shielding element and jet engine, in which such element is used

Seal structure for gas turbine rotor blade