US 2026/0266185 A1Published application

Gas turbine engine rotor stage with rotor blade damper arrangement

AssigneeRtx Corporation

InventorsDavid E. Gambardella, Benjamin B. Simpson, Jeffrey S. Beattie

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Abstract

A rotor stage for a gas turbine engine is provided that includes a disk, first and second rotor blades, a platform seal, and a damper. The first and second rotor blades are attached to the disk and adjacent. The first rotor blade has a first neck portion and a first platform, and the second rotor blade has a second neck portion and a second platform. The first rotor blade has a first lateral rail that extends laterally outward from a first neck portion surface, and has a first damper post that extends laterally outward from the first neck portion surface. The second rotor blade has a second lateral rail that extends laterally outward from a second neck portion surface, and has a second damper post that extends laterally outward from the second neck portion surface. The damper is circumferentially disposed between the first and second lateral rails.

Claims20

Dependent claims

A rotor stage for a gas turbine engine, comprising:

a disk;
a first rotor blade and a second rotor blade attached to the disk so they are adjacent one another;
wherein the first rotor blade has a first neck portion and a first platform, and the second rotor blade has a second neck portion and a second platform;
wherein the first rotor blade has a first lateral rail that extends laterally outward from a first neck portion surface, and has a first damper post that extends laterally outward from the first neck portion surface;
wherein the second rotor blade has a second lateral rail that extends laterally outward from a second neck portion surface, and has a second damper post that extends laterally outward from the second neck portion surface;
wherein the first lateral rail and the first damper post are spaced apart from and independent of the first platform, and the second lateral rail and the second damper post are spaced apart from and independent of the second platform;
a platform seal;
and
a damper;
wherein the damper is circumferentially disposed between the first lateral rail and the second lateral rail;
and
wherein axial movement of the damper is constrained by the first damper post and the second damper post.

9 more elements

A gas turbine engine, comprising:

a compressor section;
a combustor section;
and
a turbine section, the turbine section having a first rotor stage and a second rotor stage;
wherein the first rotor stage includes:
a disk;
a first rotor blade and a second rotor blade attached to the disk so they are adjacent one another;
wherein the first rotor blade has a first neck portion and a first platform, and the second rotor blade has a second neck portion and a second platform;
wherein the first rotor blade has a first lateral rail that extends laterally outward from a first neck portion surface, and has a first damper post that extends laterally outward from the first neck portion surface;
wherein the second rotor blade has a second lateral rail that extends laterally outward from a second neck portion surface, and has a second damper post that extends laterally outward from the second neck portion surface;
wherein the first lateral rail and the first damper post are spaced apart from and independent of the first platform, and the second lateral rail and the second damper post are spaced apart from and independent of the second platform;
a platform seal;
and
a damper;
wherein the damper is circumferentially disposed between the first lateral rail and the second lateral rail;
and
wherein axial movement of the damper is constrained by the first damper post and the second damper post.

14 more elements

Dependencies are inferred from the claim text.