Seal configuration to prevent rotor lock
The present disclosure relates to gas turbine engine and seal configurations, and components for a gas turbine engine. In one embodiment, a seal for a gas turbine engine includes a rotary seal element, the rotary seal element configured to rotate during operation of a gas turbine engine, and a stationary seal element having an annular seal surface. The stationary seal element includes a first area of the annular seal surface configured to engage with the rotary seal element, and the stationary seal element includes a second area of the annular seal surface configured to provide reduced resistance to the rotary seal element during a flight windmilling event.
1. A seal assembly for a gas turbine engine, the seal assembly comprising:
a stationary seal element including:
(i) a heightwise outer segment having a first height and extending continuously from a leading edge to a trailing edge; and
(ii) a heightwise inner segment having a second height and a heightwise inner surface that forms an annular surface, the heightwise inner segment formed of three mutually contacting portions including:
(a) a first portion being integral with the heightwise outer segment and extending to the leading edge;
(b) a second portion that is a first abradable portion extending aft from the first portion; and
(c) a third portion that is a second abradable portion extending aft from the first abradable portion to the trailing edge and providing a reduced resistance to wear relative to the second portion;
wherein the first abradable portion and the second abradable portion each have a heightwise outer surface that contacts the heightwise outer segment; and
a rotary seal element that rotates during operation of the gas turbine engine, the rotary seal element comprising a knife edge that faces the annular surface, wherein the stationary seal element and the rotary seal element are configured such that the rotary seal element:
(i) engages the first abradable portion when the rotary seal element rotates under engine power; and
(ii) engages the second abradable portion when the rotary seal element rotates during an engine wind-milling event.
2. The seal assembly of claim 1 , wherein the first abradable portion and the second abradable portion include a honeycomb material.
3. The seal assembly of claim 1 wherein the stationary seal element has a rectangular cross section.
4. A gas turbine engine comprising:
a plurality of blade elements, a casing; and
a seal assembly between the plurality of blade elements and casing, the seal assembly comprising:
a stationary seal element including: (i) a heightwise outer segment having a first height and extending continuously from a leading edge to a trailing edge; and (ii) a heightwise inner segment having a second height and a heightwise inner surface that forms an annular surface, the heightwise inner segment formed of three mutually contacting portions including: (a) a first portion being integral with the heightwise outer segment and extending to the leading edge; (b) a second portion that is a first abradable portion extending aft from the first portion; and (c) a third portion that is a second abradable portion extending aft from the first abradable portion to the trailing edge and providing a reduced resistance to wear relative to the second portion; wherein the first abradable portion and the second abradable portion each have a heightwise outer surface that contacts the heightwise outer segment; and
a rotary seal element that rotates during operation of the gas turbine engine, the rotary seal element comprising a knife edge that faces the annular surface, wherein the stationary seal element and the rotary seal element are configured such that the rotary seal element: (i) engages the first abradable portion when the rotary seal element rotates under engine power; and (ii) engages the second abradable portion when the rotary seal element rotates during an engine wind-milling event.
5. The gas turbine engine of claim 4 , wherein the first abradable portion and the second abradable portion include a honeycomb material.
6. The gas turbine engine of claim 4 wherein the stationary seal element has a rectangular cross section.