Globe butterfly valve

Patent metadata

Field	Value
Publication number	US-10823302-B2
Application number	US-201816123336-A
Country	US
Kind code	B2
Filing date	Sep 6, 2018
Priority date	Sep 6, 2018
Publication date	Nov 3, 2020
Grant date	Nov 3, 2020

Abstract

An aspect includes a globe butterfly valve that includes a valve inlet, a valve outlet, a globe housing with a spherical body between the valve inlet and the valve outlet, and a globe butterfly valve disc operably disposed within the globe housing. The globe housing has a larger interior diameter than an inlet diameter of the valve inlet and an outlet diameter of the valve outlet. The globe butterfly valve disc is configured to block a flow path between the valve inlet and the valve outlet responsive to an outer edge of the globe butterfly valve disc being positioned proximate to an interior surface of the globe housing between the valve inlet and the valve outlet.

First claim

What is claimed is:

1. A gas turbine engine system comprising:
a gas turbine engine comprising a compressor section, a combustor section, and a turbine section, the gas turbine engine configured to produce a first airflow and a second airflow:
a first pneumatic tube coupled to the gas turbine engine;
a second pneumatic tube coupled to the gas turbine engine; and
a dual valve system comprising:
a valve body coupled to the first pneumatic tube;
a valve disc operably disposed within the valve body;
a globe housing comprising a spherical body coupled to the second pneumatic tube;
a globe butterfly valve disc operably disposed within the globe housing; and
a linkage system operably coupled to the valve disc and the globe butterfly valve disc, wherein the globe housing differs in geometry from the valve body such that opening of a first flow area between the valve disc and the valve body to receive the first airflow from the first pneumatic tube occurs prior to opening of a second flow area between to the globe butterfly valve disc and the globe housing to receive the second airflow from the second pneumatic tube responsive to movement of the linkage system.

2. The gas turbine engine system of claim 1 , wherein the first flow area controls delivery of the first airflow to a first airflow use, and the second flow area controls delivery of the second airflow to a second airflow use.

3. The gas turbine engine system of claim 1 , wherein the valve body and the globe housing are arranged substantially parallel to each other.

4. The gas turbine engine system of claim 1 , wherein the globe butterfly valve disc comprises a pivot point, and the globe butterfly valve disc is operable to rotate about the pivot point within the globe housing.

5. The gas turbine engine system of claim 1 , wherein the interior surface ofthe globe housing forms a hysteresis region of rotation that blocks the second flow area during rotation of the globe butterfly valve disc within the hysteresis region.

6. The gas turbine engine system of claim 5 , wherein the second flow area is maximized responsive to rotation of the globe butterfly valve disc by about ninety degrees from a midpoint of the hysteresis region.

7. The gas turbine engine system of claim 1 , wherein the globe housing is between a valve inlet and a valve outlet, the globe housing having a larger interior diameter than an inlet diameter of the valve inlet and an outlet diameter of the valve outlet.

8. The gas turbine engine system of claim 1 , wherein the globe housing has a larger interior diameter than the valve body.

9. The gas turbine engine system of claim 1 , wherein the valve body and the valve disc comprise a first butterfly valve, and the globe housing and the globe butterfly valve disc comprise a second butterfly valve.

10. The gas turbine engine system of claim 1 , further comprising an actuator operably coupled to the linkage system.

11. The gas turbine engine system of claim 1 , wherein the valve disc is configured to rotate about a first pivot point, the globe butterfly valve disc is configured to rotate about a second pivot point, and the linkage system comprises a first crank linkage operably coupled to the first pivot point of the valve disc, a second crank linkage operably coupled to the second pivot point of the globe butterfly valve disc, and an armature coupled to the first crank linkage at a third pivot point and coupled to the second crank linkage at a fourth pivot point.

12. A method of operating a dual valve system, the method comprising:
receiving a first airflow from a gas turbine engine at a first pneumatic tube coupled to a valve body of the dual valve system;
receiving a second airflow from the gas turbine engine at a second pneumatic tube coupled to a globe housing of the dual valve system;
driving a valve disc to rotate in the valve body using an actuator; and
translating a rotational force of the actuator through a linkage system operably coupled to the valve disc and a globe butterfly valve disc, wherein the globe butterfly valve disc is disposed within the globe housing and the globe housing differs in geometry from the valve body such that opening of a first flow area between the valve disc and the valve body occurs prior to opening of a second flow area between to the globe butterfly valve disc and the globe housing responsive to the rotational force.

13. The method of claim 12 , wherein the valve body and the globe housing are arranged substantially parallel to each other.

14. The method of claim 12 , wherein the interior surface of the globe housing forms a hysteresis region of rotation that blocks the second flow area during rotation of the globe butterfly valve disc within the hysteresis region, and the second flow area is maximized responsive to rotation of the globe butterfly valve disc by about ninety degrees from a midpoint of the hysteresis region.

15. The method of claim 12 , wherein the globe housing is a spherical body between a valve inlet and a valve outlet, the globe housing having a larger interior diameter than an inlet diameter of the valve inlet and an outlet diameter of the valve outlet.

16. The method of claim 12 , wherein the globe housing has a larger interior diameter than the valve body.

17. The method of claim 12 , wherein the first flow area controls delivery of the first airflow to a first airflow use, and the second flow area controls delivery of the second airflow to a second airflow use.

18. The method of claim 12 , wherein the valve disc is configured to rotate about a first pivot point, the globe butterfly valve disc is configured to rotate about a second pivot point, and the linkage system comprises a first crank linkage operably coupled to the first pivot point of the valve disc, a second crank linkage operably coupled to the second pivot point of the globe butterfly valve disc, and an armature coupled to the first crank linkage at a third pivot point and coupled to the second crank linkage at a fourth pivot point.

19. A method of operating a dual valve system, the method comprising:
driving a valve disc to rotate in a valve body using an actuator; and
translating a rotational force of the actuator through a linkage system operably coupled to the valve disc and a globe butterfly valve disc, wherein the globe butterfly valve disc is disposed within a globe housing and the globe housing differs in geometry from the valve body such that opening of a first flow area between the valve disc and the valve body occurs prior to opening of a second flow area between to the globe butterfly valve disc and the globe housing responsive to the rotational force, wherein the valve body and the valve disc comprise a first butterfly valve, and the globe housing and the globe butterfly valve disc comprise a second butterfly valve.

20. The method of claim 19 , wherein the valve disc is configured to rotate about a first pivot point, the globe butterfly valve disc is configured to rotate about a second pivot point, and the linkage system comprises a first crank linkage operably coupled to the first pivot point of the valve disc, a second crank linkage operably coupled to the second pivot point of the globe butterfly valve disc, and an armature coupled to the first crank linkage at a third pivot point and coupled to the second crank linkage at a fourth pivot point.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Waddell Matthew C
• Clauson Jesse W

Classifications

• F01D11/22

  by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor · CPC title

• F16K1/221 Primary

  specially adapted operating means therefor (operating means per se F16K31/00) · CPC title

• F16K1/223

  with a plurality of valve members · CPC title

• F16K31/521

  comprising a pivoted disc or flap · CPC title

• F01D17/148

  by means of rotatable members, e.g. butterfly valves · CPC title