Break-in system for gapping and leakage control
AssigneeUnited Technologies Corporation
InventorsPaul M. Lutjen, Richard K. Hayford
Life of this patent
Estimating the term…
Abstract
A blade outer air seal for use in a gas turbine engine having an axis of rotation includes a main body having a mating face configured to face, be positioned radially outward from, and be positioned adjacent to a rotor blade of the gas turbine engine. The blade outer air seal also includes an axial member extending aft from the main body, having a first radial face configured to face a second radial face of an outer diameter platform of a stator of the gas turbine engine, and having a first abradable material coupled to the first radial face.
Claims16
A first static component for use in a gas turbine engine having an axis of rotation, the first static component comprising:
- a main body
- a mating face configured to be positioned radially outward from and face a rotor blade;
- a second abradable material coupled to the mating face and configured to form a seal with the rotor blade;
- and
- an axial member extending aft from the main body, having a first radial face configured to face a second radial face of a second static component of the gas turbine engine, and having a first abradable material coupled to the first radial face and having a same composition as the second abradable material.
A system for reducing leakage air in a gas turbine engine having an axis of rotation, the system comprising:
- a rotor blade;
- a blade outer air seal having:
- a main body,
- a mating face positioned radially outward from the rotor blade,
- a second abradable material coupled to the mating face and configured to form a seal with the rotor blade, and
- an axial member extending away from the main body, the axial member having a first radial face and one of a first abradable material coupled to the first radial face or an abrasive material coupled to the first radial face;
- and
- an outer diameter platform having a second radial face at least partially facing the first radial face and the other of the first abradable material or the abrasive material coupled to the second radial face such that the first abradable material and the abrasive material form a flow restriction,
- wherein the first abradable material has a same composition as the second abradable material.
A gas turbine engine, comprising:
- a compressor section;
- a combustor section;
- and
- a turbine section;
- wherein at least one of the compressor section or the turbine section include:
- a rotor blade;
- a stator;
- a blade outer air seal positioned radially outward from the rotor blade and having:
- a main body,
- a mating face positioned radially outward from the rotor blade,
- a second abradable material coupled to the mating face and configured to form a seal with the rotor blade, and
- an axial member extending away from the main body, the axial member having a first radial face and a first abradable material coupled to the first radial face and having a same composition as the second abradable material;
- and
- an outer diameter platform positioned radially outward from the stator and having a second radial face at least partially facing the first radial face and an abrasive material coupled to the second radial face such that the first abradable material and the abrasive material form a flow restriction.
Dependencies are inferred from the claim text.