Granted Patent B1

US 12,480,418 · App. 18/772,386 · Granted Nov 25, 2025

Inventor: Todd A. Davis (Tolland, CT)

Assignee: RTX CORPORATION

F01D11/005F01D11/003F01D25/183F05D2220/32F05D2240/55

Abstract

Claims (52)

1. 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.

2. The seal assembly as recited in claim 1 , wherein:

the at least one spring carrier includes a plurality of spring carriers distributed about the assembly axis; and

the at least one spring member includes a plurality of spring members received in the spring pockets of the respective spring carriers.

3. The seal assembly as recited in claim 2 , wherein the spring carriers are radially outward of the annular contacting-type seal member relative to the assembly axis.

4. The seal assembly as recited in claim 3 , wherein the spring pockets are dimensioned such that the spring members extend past the annular seal face relative to the assembly axis.

5. The seal assembly as recited in claim 1 , wherein the annular contacting-type seal member is non-metallic.

6. The seal assembly as recited in claim 5 , wherein the annular contacting-type seal member is a carbon seal.

7. The seal assembly as recited in claim 1 , wherein the at least one spring carrier and the respective spring pocket are cylindrical.

8. The seal assembly as recited in claim 1 , wherein the at least one spring member is a coil spring.

9. The seal assembly as recited in claim 1 , wherein the seal land is associated with a bearing compartment.

10. 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.

11. The gas turbine engine as recited in claim 10 , wherein the seal member is an annular carbon seal extending about the engine axis.

12. The gas turbine engine as recited in claim 10 , further comprising:

a bearing assembly including at least one bearing in a bearing compartment and a rotatable member establishing the seal land.

13. The gas turbine engine as recited in claim 10 , wherein the support is mechanically attached to a static structure of the engine.

14. The gas turbine engine as recited in claim 10 , wherein:

the at least one spring carrier includes a plurality of spring carriers distributed about the engine axis; and

the at least one spring member includes a plurality of spring members received in the spring pockets of the respective spring carriers.

15. 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.

16. The method as recited in claim 15 ,

wherein the contacting-type seal member comprises a carbon material.

17. The method as recited in claim 15 , wherein:

the interface is established along a bearing compartment; and

the bearing compartment includes at least one bearing that supports a rotatable shaft.

Assignments (1)

References Cited (9)