US 9,068,469 B2Granted

Gas turbine engines with abradable turbine seal assemblies

AssigneeHoneywell International Inc.

InventorsBradley Reed Tucker, Jason Smoke, Mark C. Morris

Life of this patent

Estimating the term…

Loading patent…

Abstract

A turbine section of a gas turbine engine includes a housing, a rotor assembly, and a seal assembly. The rotor assembly includes a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path. The stator assembly includes a stator platform with a stator vane that extends from the stator platform into the mainstream hot gas flow path. The seal assembly includes a first flow discourager extending in a first direction from the rotor platform, a second flow discourager extending in a second direction from the stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction, a hard coating applied to the first flow discourager, and an abradable coating applied to the second flow discourager.

Claims18

Dependent claims

A turbine section of a gas turbine engine, comprising:

a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow;
a rotor assembly including a rotor disk, a rotor platform coupled to the rotor disk, and a rotor blade extending from the rotor platform into the mainstream hot gas flow path;
a first stator assembly positioned adjacent to the rotor assembly on a downstream side and forming a first turbine disk cavity with the rotor disk of the rotor assembly, the first stator assembly including a first stator platform with a first stator vane that extends from the first stator platform into the mainstream hot gas flow path;
a second stator assembly positioned adjacent to the rotor assembly on an upstream side and forming a second turbine disk cavity with the rotor disk of the rotor assembly, the second stator assembly including a second stator platform with a second stator vane that extends from the second stator platform into the mainstream hot gas flow path;
and
a seal assembly comprising
a first flow discourager extending in a downstream direction from the rotor platform,
a second flow discourager extending in an upstream direction from the first stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction,
a first hard coating applied to the first flow discourager,
a first abradable coating applied to the second flow discourager,
a third flow discourager extending in the upstream direction from the rotor platform,
a fourth flow discourager extending in the downstream direction from the second stator platform, the fourth flow discourager axially overlapping the third flow discourager such that the third flow discourager is interior to the fourth flow discourager in the radial direction,
a second hard coating applied to the fourth flow discourager, and
a second abradable coating applied to the third flow discourager.

11 more elements

A seal assembly for a turbine section of a gas turbine engine, the turbine section including first and second stator assemblies such that the first stator assembly has a first stator platform and the second stator assembly has a second stator platform and a rotor assembly with a rotor platform, the seal assembly comprising:

a first flow discourager extending in a downstream direction from the rotor platform;
a second flow discourager extending in an upstream direction from the first stator platform, the first flow discourager axially overlapping the second flow discourager such that the second flow discourager is interior to the first flow discourager in a radial direction;
a first hard coating applied to the first flow discourager;
a first abradable coating applied to the second flow discourager;
a third flow discourager extending in the upstream direction from the rotor platform;
a fourth flow discourager extending in the downstream direction from the second stator platform, the fourth flow discourager axially overlapping the third flow discourager such that the third flow discourager is interior to the fourth flow discourager in the radial direction;
a second hard coating applied to the fourth flow discourager;
and
a second abradable coating applied to the third flow discourager.

6 more elements

Dependencies are inferred from the claim text.

Facts

Application: 13/224,035Filed 1 Sep 2011
Published: US 2013/0058768 A17 Mar 2013
Granted: 30 Jun 2015
Term ends: Not estimatedThe source records don’t support an estimate.

Classification11 codes

F01D 11/122
Using a rubstrip, e.g. erodible. deformable or resiliently-biased part: with erodable or abradable material
F01D 11/006
Sealing means between non relatively rotating elements: sealing the gap between rotor blades or blades and rotor
F05D 2230/313
Layer deposition: by physical vapour deposition
F05D 2240/55
Components: seals