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 an annular seal carrier extending about an assembly axis. An annular contacting-type seal member may be secured along a shelf of 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 an annular 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.
Claims17
A seal assembly for a gas turbine engine comprising:
- an annular seal carrier extending about an assembly axis;
- an annular contacting-type seal member secured along a shelf of the annular seal carrier;
- at least one spring carrier extending from the annular 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 is arranged to bias an annular seal face of the annular contacting-type seal member against a seal land at an interface;
- and
- an annular support securable to the annular seal carrier, the annular support extending about the assembly axis;
- wherein the at least one spring carrier extends past the annular 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 annular support such that the spring carrier is biased away from the annular support;
- wherein a maximum distance between the annular seal face and the spring land in an assembled configuration establishes a first length relative to the assembly axis;
- wherein a maximum distance between a floor of the spring pocket and the spring land in the assembled configuration establishes a second length;
- and
- wherein the second length is at least 95 percent of the first length.
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 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;
- wherein a maximum distance between the interface and a spring land of the support in an assembled configuration establishes a first length relative to the engine axis;
- wherein a maximum distance between a floor of the respective spring pocket and the spring land in the assembled configuration establishes a second length relative to the engine axis;
- and
- wherein the second length is at least 95 percent of the first length.
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 respective pockets of one or more spring carriers that extend from the seal carrier;
- 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 a maximum distance between the interface and the spring land in an assembled configuration establishes a first length relative to the engine axis;
- wherein a maximum distance between a floor of the respective spring pocket and a spring land of the support in the assembled configuration establishes a second length relative to the engine axis;
- and
- wherein the second length is at least 95 percent of the first length.
Dependencies are inferred from the claim text.