Seal assembly for gas turbine engines
AssigneeRtx Corporation
InventorTodd A. Davis
Life of this patent
Estimating the term…
Abstract
A seal assembly for a gas turbine engine may include a seal carrier extending about an assembly axis. A contacting-type seal member may be secured along the seal carrier. At least one spring carrier may extend from the seal carrier. At least one spring member may be received in a spring pocket of the respective at least one spring carrier. The at least one spring member may be arranged to bias a seal face of the seal member against a seal land at an interface. The at least one spring carrier may extend past the seal face relative to the assembly axis. A method of sealing for a gas turbine engine is also disclosed.
Claims20
A seal assembly for a gas turbine engine comprising:
- a seal carrier extending about an assembly axis;
- a contacting-type seal member along the seal carrier;
- at least one spring carrier coupled to the seal carrier;
- at least one spring member received in a spring pocket of the respective at least one spring carrier, wherein the at least one spring member abuts a floor of the spring pocket, and wherein the at least one spring member is arranged to bias a seal face of the contacting-type seal member against a seal land at an interface;
- and
- a support extending about the assembly axis;
- wherein a portion of the at least one spring carrier extends past the seal face relative to the assembly axis;
- wherein the at least one spring member is captured between the respective at least one spring carrier and a spring land of the support;
- and
- wherein the floor of the spring pocket is moveable between a first position on a first side of the seal land and a second position on a second side of the seal land in response to biasing of the spring carrier by the spring member away from the support.
A gas turbine engine comprising:
- a compressor section including a compressor;
- a turbine section including a turbine that drives the compressor;
- and
- a seal assembly comprising:
- a seal carrier secured to a support;
- at least one spring carrier extending from the seal carrier along an engine axis;
- a seal member secured to the seal carrier;
- and
- at least one spring member received in a spring pocket of the respective at least one spring carrier and seated against the support, wherein the at least one spring member abuts a floor of the spring pocket;
- wherein the at least one spring member is arranged to bias the seal member against a seal land at an interface such that the at least one spring carrier extends past the interface relative to the engine axis;
- and
- wherein the floor of the spring pocket is moveable between a first position on a first side of the seal land and a second position on a second side of the seal land in response to biasing of the spring carrier by the spring member away from the support.
A method of sealing for a gas turbine engine comprising:
- securing a seal carrier to a support such that one or more spring members are captured in one or more respective pockets of one or more spring carriers that extend from the seal carrier, wherein the one or more spring members abut a floor of the respective one or more spring pockets;
- securing a contacting-type seal member to the seal carrier;
- and
- biasing the contacting-type seal member against a rotatable seal land at an interface such that the one or more spring carriers extend past the interface relative to an engine axis;
- wherein the floor of the one or more spring pockets is moveable between a first position on a first side of the seal land and a second position on a second side of the seal land in response to the biasing.
Dependencies are inferred from the claim text.