Flap seal for gas turbine engine movable nozzle flap
A gas turbine engine nozzle includes a flap movable relative to a structure. A seal assembly is supported by one of the structure and the flap and includes a seal hinged about an axis. The seal has a sealing profile engaging a seal land of the other of the structure and the flap. A biasing member is configured to urge the hinged seal toward the seal land. A method of sealing a nozzle flap includes supporting a seal relative to a structure along an axis. The seal is urged toward a nozzle flap. The seal rotates about the axis to maintain engagement between the seal and the nozzle flap in response to the urging step.
1. A method of sealing a cavity between a nozzle flap and a fixed structure, the method comprising the steps of:
providing a seal that extends between first and second ends, the first end provides a hinge portion, and the second end includes a laterally extending sealing profile;
supporting the hinged portion relative to a fixed structure along an axis to provide a V-shape with the seal and the fixed structure;
biasing the seal toward a seal land on a nozzle flap with a spring biasing member providing a spring biasing force and with pressurized fluid; and
rotating the seal about the axis and relative to the nozzle flap and the fixed structure to maintain sealing engagement between the sealing profile and the seal land in response to the spring biasing step and seal the cavity between the nozzle flap and the fixed structure.
2. The method according to claim 1 , wherein the spring biasing step includes applying a fluid pressure to the seal.
3. The method according to claim 1 , wherein the spring biasing step includes biasing the seal with a spring element.
4. A gas turbine engine nozzle comprising:
a static hood;
a seal holder extending from the static hood in a first axial direction to an end providing an pivotal axis, the seal holder secured to the static hood by fastening elements to provide a fixed structure;
a flap movable relative to the fixed structure;
a seal hinged about the pivotal axis and extending from the pivotal axis in a second axial direction opposite the first axial direction to a sealing profile engaging the flap, the seal and the seal holder configured in a V-shape, the seal rotatable about the pivotal axis and movable relative to the flap and the seal holder, the seal providing a pressurized backside facing the seal holder; and
a spring biasing member arranged at the pressurized backside of the seal and configured to continuously urge the seal toward and maintain engagement with a seal land on the flap.
5. The gas turbine engine nozzle according to claim 4 , wherein the flap has first and second nozzle positions.
6. The gas turbine engine nozzle according to claim 4 , wherein the fastening elements is at least one of a rivet and a bolt.
7. The gas turbine engine nozzle according to claim 4 , wherein the seal profile is linear.
8. The gas turbine engine nozzle according to claim 4 , wherein the seal is pivotally secured to the seal holder by a pin providing the pivotal axis, and the spring biasing member is supported by the pin and arranged laterally between the seal holder and the seal.
9. The gas turbine engine nozzle according to claim 8 , wherein the spring biasing member is a torsion spring.
10. The gas turbine engine nozzle according to claim 8 , wherein the spring biasing member is a finger spring.
11. The gas turbine engine nozzle according to claim 10 , wherein the finger spring includes first and second ends, the finger spring first end supported by one of the static hood and the seal holder and the finger spring second end engages the seal and is movable relative to the finger spring first end.
12. The gas turbine engine nozzle according to claim 10 , wherein the finger spring is generally V-shaped providing first and second legs joined by an intermediate portion, the intermediate portion supported by the pin, the first leg engaging one of the static hood and the seal holder, and the second leg engaging the seal.