Passive centrifugal bleed valve system for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-11008979-B2
Application number	US-201916425016-A
Country	US
Kind code	B2
Filing date	May 29, 2019
Priority date	May 29, 2019
Publication date	May 18, 2021
Grant date	May 18, 2021

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.

First claim

What is claimed:

1. 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.

2. The valve as recited in claim 1 , wherein the cantilevered valve is integral with the inner section.

3. The valve as recited in claim 1 , wherein the cantilevered valve is sandwiched between the inner section and a seal section.

4. The valve as recited in claim 3 , wherein the cantilevered valve seals the flow control inlet orifice in response to a second centrifugal force less than the first centrifugal force.

5. The valve as recited in claim 1 , wherein the inner section is an inner portion of a shaft and the outer section is an outer portion of the shaft.

6. The valve as recited in claim 1 , wherein the seal land geometry is arcuate.

7. 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.

8. 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.

9. The gas turbine engine as recited in claim 8 , wherein the passive centrifugal bleed valve system comprises at least one valve that opens in response to the first centrifugal force.

10. The gas turbine engine as recited in claim 8 , wherein the passive centrifugal bleed valve system comprises at least one valve that closes in response to the first centrifugal force.

11. The gas turbine engine as recited in claim 8 , wherein the passive centrifugal bleed valve system comprises at least one valve that opens in response to the second centrifugal force.

12. The gas turbine engine as recited in claim 8 , wherein the passive centrifugal bleed valve system comprises at least one valve that closes in response to the second centrifugal force.

13. The gas turbine engine as recited in claim 8 , wherein the second centrifugal force is a takeoff power condition.

14. 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.

15. The method as recited in claim 14 , wherein the first configuration comprises passively opening at least one valve in response to a first centrifugal force.

16. The method as recited in claim 14 , wherein the second configuration comprises passively opening at least one valve in response to a second centrifugal force.

17. 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.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Mccaffrey Michael G
• Propheter-Hinckley Tracy A

Classifications

• Y02T10/12

  Improving ICE efficiencies · CPC title

• F05D2260/77

  the adjusting mechanism driven or triggered by centrifugal forces · CPC title

• F04D27/0215

  Arrangements therefor, e.g. bleed or by-pass valves · CPC title

• F02M23/06 Primary

  dependent on engine speed · CPC title

• F02M23/006 Primary

  Valves specially shaped for supplying secondary air · CPC title