Shared load path blade outer air seal
A blade outer airseal (BOAS) assembly of a gas turbine engine includes a plurality of BOAS segments arrayed circumferentially about the engine central longitudinal axis, and a plurality of BOAS carriers located radially outboard of the plurality of BOAS segments. Each BOAS carrier is supportive of at least one BOAS segment. The BOAS assembly includes plurality of adjustment levers. Each adjustment lever is operably connected to at least two BOAS carriers of the plurality of BOAS carriers. Rotation of each adjustment lever about a respective pivot axis urges movement of the plurality of BOAS segments in a radial direction thereby adjusting a radial gap between the turbine rotor and the plurality of BOAS segments.
1 . A blade outer airseal (BOAS) assembly of a gas turbine engine, comprising:
a plurality of BOAS segments arrayed circumferentially about an engine central longitudinal axis;
a plurality of BOAS carriers disposed radially outboard of the plurality of BOAS segments, each of the plurality of BOAS carriers supportive of at least one BOAS segment of the plurality of BOAS segments; and
a plurality of adjustment levers, each adjustment lever of the plurality of adjustment levers operably connected to at least two BOAS carriers of the plurality of BOAS carriers;
wherein rotation of each adjustment lever of the plurality of adjustment levers about a respective pivot axis which extends parallel to the engine central longitudinal axis urges movement of the at least two BOAS carriers in a radial direction thereby adjusting a radial gap between a turbine rotor and the plurality of BOAS segments;
wherein each adjustment lever of the plurality of adjustment levers is a unitary member and includes a first lever arm extending in a first direction from the respective pivot axis of each adjustment lever of the plurality of adjustment levers and a second lever arm extending in a second direction from the respective pivot axis of each adjustment lever of the plurality of adjustment levers opposite the first direction;
wherein the first lever arm of at least one adjustment lever of the plurality of adjustment levers is engaged with complementary engagement features of the at least two BOAS carriers that are circumferentially adjacent to each other;
wherein, for each adjustment lever of the plurality of adjustment levers, a pin rotatably securing the adjustment lever to a casing element of the gas turbine engine, and the pin defining the respective pivot axis; and
wherein each adjustment lever of the plurality of adjustment levers is located between a casing flange and an aft flange located rearward of the casing flange, and, for each adjustment lever of the plurality of adjustment levers, the pin extending through all of the casing flange, the aft flange, and the adjustment lever to retain the adjustment lever.
2 . The BOAS assembly of claim 1 , wherein the complementary engagement features are slots in respective circumferential ends of the at least two BOAS carriers that are circumferentially adjacent to each other, the first lever arm of the at least one adjustment lever extending at least partially through the slots.
3 . The BOAS assembly of claim 1 , further comprising an actuator operably connected to the second lever arm of the at least one adjustment lever of the plurality of adjustment levers, the actuator configured to urge rotation of the at least one adjustment lever about the respective pivot axis of the at least one adjustment lever.
4 . The BOAS assembly of claim 1 , further comprising one or more retention features to limit radial movement of the at least one BOAS segment of the plurality of BOAS segments.
5 . A turbine section of a gas turbine engine, comprising:
a turbine rotor disposed at an engine central longitudinal axis; and
a blade outer airseal (BOAS) assembly disposed radially outboard of the turbine rotor, the BOAS assembly including:
a plurality of BOAS segments arrayed circumferentially about the engine central longitudinal axis;
a plurality of BOAS carriers disposed radially outboard of the plurality of BOAS segments, each BOAS carrier of the plurality of BOAS carriers supportive of at least one BOAS segment of the plurality of BOAS segments; and
a plurality of adjustment levers, each adjustment lever of the plurality of adjustment levers operably connected to at least two BOAS carriers of the plurality of BOAS carriers;
wherein rotation of each adjustment lever of the plurality of adjustment levers about a respective pivot axis which extends parallel to the engine central longitudinal axis urges movement of the at least two BOAS carriers in a radial direction thereby adjusting a radial gap between the turbine rotor and the plurality of BOAS segments;
wherein each adjustment lever of the plurality of adjustment levers is a unitary member and includes a first lever arm extending in a first direction from the respective pivot axis of each adjustment lever of the plurality of adjustment levers and a second lever arm extending in a second direction from the respective pivot axis of each adjustment lever of the plurality of adjustment levers opposite the first direction;
wherein the first lever arm of at least one adjustment lever of the plurality of adjustment levers is engaged with complementary engagement features of the at least two BOAS carriers that are circumferentially adjacent to each other;
wherein, for each adjustment lever of the plurality of adjustment lever, a pin rotatably securing the adjustment lever to a casing element of the gas turbine engine, and the pin defining the respective pivot axis; and
wherein each adjustment lever of the plurality of adjustment levers is located between a casing flange and an aft flange located rearward of the casing flange, and, for each adjustment lever of the plurality of adjustment levers, the pin extending through all of the casing flange, the aft flange, and the adjustment lever to retain the adjustment lever.
6 . The turbine section of claim 5 , wherein the complementary engagement features are slots in respective circumferential ends of the at least two BOAS carriers that are circumferentially adjacent to each other, the first lever arm of the at least one adjustment lever extending at least partially through the slots.
7 . The turbine section of claim 5 , further comprising an actuator operably connected to the second lever arm of the at least one adjustment lever of the plurality of adjustment levers, the actuator configured to urge rotation of the at least one adjustment lever about the respective pivot axis of the at least one adjustment lever.
8 . The turbine section of claim 5 , further comprising one or more retention features to limit radial movement of the at least one BOAS segment of the plurality of BOAS segments.
9 . A gas turbine engine, comprising:
a combustor; and
a turbine section driven by combustion products from the combustor, the turbine section including:
a turbine rotor disposed at an engine central longitudinal axis; and
a blade outer airseal (BOAS) assembly disposed radially outboard of the turbine rotor, the BOAS assembly including:
a plurality of BOAS segments arrayed circumferentially about the engine central longitudinal axis;
a plurality of BOAS carriers disposed radially outboard of the plurality of BOAS segments, each BOAS carrier of the plurality of BOAS carriers supportive of at least one BOAS segment of the plurality of BOAS segments; and
a plurality of adjustment levers, each adjustment lever of the plurality of adjustment levers operably connected to at least two BOAS carriers of the plurality of BOAS carriers;
wherein rotation of each adjustment lever of the plurality of adjustment levers about a respective pivot axis which extends parallel to the engine central longitudinal axis urges movement of the at least two BOAS carriers in a radial direction thereby adjusting a radial gap between the turbine rotor and the plurality of BOAS segments;
wherein each adjustment lever of the plurality of adjustment levers is a unitary member and includes a first lever arm extending in a first direction from the respective pivot axis of each adjustment lever of the plurality of adjustment levers and a second lever arm extending in a second direction from the respective pivot axis of each adjustment lever of the plurality of adjustment levers opposite the first direction;
wherein the first lever arm of at least one adjustment lever of the plurality of adjustment levers is engaged with complementary engagement features of the at least two BOAS carriers that are circumferentially adjacent to each other;
wherein, for each adjustment lever of the plurality of adjustment levers, a pin rotatably securing the adjustment lever to a casing element of the gas turbine engine, and the pin defining the respective pivot axis; and
wherein each adjustment lever of the plurality of adjustment levers is located between a casing flange and an aft flange located rearward of the casing flange, and, for each adjustment lever of the plurality of adjustment levers, the pin extending through all of the casing flange, the aft flange, and the adjustment lever to retain the adjustment lever.
10 . The gas turbine engine of claim 9 , wherein the complementary engagement features are slots in respective circumferential ends of the at least two BOAS carriers that are circumferentially adjacent to each other, the first lever arm of the at least one adjustment lever extending at least partially through the slots.
11 . The gas turbine engine of claim 9 , further comprising an actuator operably connected to the second lever arm of the at least one adjustment lever of the plurality of adjustment levers, the actuator configured to urge rotation of the at least one adjustment lever about the respective pivot axis of the at least one adjustment lever.