Passive centrifugal bleed valve system for a gas turbine engine
AssigneeRaytheon Technologies Corporation
InventorsMichael G. McCaffrey, Tracy A. Propheter-Hinckley
Life of this patent
Estimating the term…
Abstract
A passive centrifugal valve for a gas turbine engine. The passive centrifugal valve includes an inner section with a flow control inlet orifice, a cantilevered valve adjacent to the flow control inlet orifice, and an outer section with a seal land geometry that operates to at least partially support the cantilevered valve in response to a first centrifugal force that deflects the cantilevered valve away from the flow control inlet orifice.
Claims17
A passive centrifugal valve for a gas turbine engine rotational component, comprising:
- an inner section with a flow control inlet orifice;
- a cantilevered valve adjacent to the flow control inlet orifice;
- an outer section comprising a seal land geometry that operates to at least partially support the cantilevered valve in response to a first centrifugal force that deflects the cantilevered valve away from the flow control inlet orifice;
- and
- a flow control sleeve within the flow control inlet orifice, wherein the cantilevered valve seals with the flow control sleeve in response to a second centrifugal force less than the first centrifugal force.
A passive centrifugal valve for a gas turbine engine rotational component, comprising:
- an inner section with a flow control inlet orifice;
- a cantilevered valve adjacent to the flow control inlet orifice;
- and
- an outer section comprising a seal land geometry that operates to at least partially support the cantilevered valve in response to a first centrifugal force that deflects the cantilevered valve away from the flow control inlet orifice, wherein the inner section comprises a bleed passage.
A gas turbine engine, comprising:
- a turbine section;
- a secondary airflow circuit in communication with the turbine section;
- and
- a passive centrifugal bleed valve system within a rotational component of the gas turbine engine operable to adapt the secondary airflow circuit to a first configuration in response to a first centrifugal force and to a second configuration in response to a second centrifugal force, wherein the first centrifugal force is an idle power condition.
A method of adapting a secondary airflow circuit for a gas turbine engine, the method comprising:
- passively adapting the secondary airflow circuit to a first configuration in response to a first operational condition, wherein the first configuration comprises passively opening a diffuser air control valve;
- and
- passively adapting the secondary airflow circuit to a second configuration in response a second operational condition.
A method of adapting a secondary airflow circuit for a gas turbine engine, the method comprising:
- passively adapting the secondary airflow circuit to a first configuration in response to a first operational condition;
- and
- passively adapting the secondary airflow circuit to a second configuration in response a second operational condition, wherein the second configuration comprises passively opening a secondary airflow control valve.
Dependencies are inferred from the claim text.