Pneumatic circuit breaker based self resetting passive overspeed control valve for turbine pump assembly

Patent metadata

Field	Value
Publication number	US-11286887-B2
Application number	US-201514695082-A
Country	US
Kind code	B2
Filing date	Apr 24, 2015
Priority date	Apr 24, 2015
Publication date	Mar 29, 2022
Grant date	Mar 29, 2022

Abstract

A turbine pump assembly has a turbine, a centrifugal pump, a passive electrical speed control system, and a pneumatic circuit breaker. The pneumatic circuit breaker has a plurality of elements that are configured to move to a position blocking an outlet duct of the turbine when a flow velocity exceeds a predetermined threshold. A rocket thrust vector control system is also disclosed.

First claim

What is claimed is:

1. A turbine pump assembly, comprising:
a turbine configured to drive a centrifugal pump;
a passive electrical speed control system configured to limit a speed of the turbine; and
a pneumatically actuated circuit breaker arranged in an outlet duct of the turbine having a plurality of elements that are configured to move to a position blocking the outlet duct when a flow velocity exceeds a predetermined threshold, wherein the circuit breaker has at least one spring attached to at least one of the plurality of elements, and the spring holds the at least one element in a closed position when the flow velocity is below the predetermined threshold.

2. The turbine pump assembly of claim 1 , wherein the pneumatically actuated circuit breaker defines a teardrop shape when the plurality of elements are in a closed position.

3. The turbine pump assembly of claim 1 , wherein the turbine is powered by a propellant provided by a main engine turbo-pump of a vehicle.

4. The turbine pump assembly of claim 3 , wherein the propellant is hydrogen gas.

5. The turbine pump assembly of claim 1 , wherein the passive electrical speed control system further comprises a valve configured to meter a flow of propellant to the turbine.

6. The turbine pump assembly of claim 1 , wherein the passive electrical speed control system comprises a permanent magnet generator and a valve control solenoid.

7. The turbine pump assembly of claim 1 , wherein the predetermined threshold is a flow velocity that will occur when the turbine is in an unloaded condition.

8. The turbine pump assembly of claim 1 , wherein the pneumatically actuated circuit breaker is configured to automatically reset to a closed position when pressure in the turbine pump assembly is reduced.

9. The turbine pump assembly of claim 1 , wherein the pneumatically actuated circuit breaker is a passive circuit breaker.

10. The turbine pump assembly of claim 1 , wherein the plurality of elements are configured to move in response to a pressure difference between a stagnation pressure within the pneumatically actuated circuit breaker and a pressure of flow around the pneumatically actuated circuit breaker.

11. The turbine pump assembly of claim 1 , wherein the predetermined threshold is a flow velocity that will occur when the passive electrical turbine speed control fails.

12. The turbine pump assembly of claim 1 , wherein the turbine is configured to stop operating when the plurality of elements are in the position blocking the outlet duct.

13. The turbine pump assembly of claim 1 , wherein the turbine and the centrifugal pump are configured to rotate between 90,000 rpm and 140,000 rpm on a common shaft.

14. A rocket thrust vector control system, comprising:
an engine nozzle configured to receive fluid from a centrifugal pump;
a turbine pump assembly having a turbine configured to drive the centrifugal pump, a passive electrical speed control system configured to limit a speed of the turbine; and
a pneumatically actuated circuit breaker arranged in an outlet duct of the turbine, wherein the circuit breaker has a plurality of elements configured to move to a position blocking the outlet duct when a flow velocity exceeds a predetermined threshold, wherein the circuit breaker has at least one spring attached to at least one of the plurality of elements, and the spring holds the at least one element in a closed position when the flow velocity is below the predetermined threshold.

15. The rocket thrust vector control system as recited in claim 14 , wherein the predetermined threshold is a flow velocity that occurs when the turbine is in an unloaded condition.

16. The rocket thrust vector control system as recited in claim 14 , wherein the turbine is powered by a propellant provided by a main engine turbo-pump of a vehicle.

17. The rocket thrust vector control system of claim 14 , wherein the pneumatically actuated circuit breaker is configured to automatically reset to a closed position when pressure in the turbine pump assembly is reduced.

18. The rocket thrust vector control system of claim 14 , wherein the pneumatically actuated circuit breaker is a passive circuit breaker.

19. The rocket thrust vector control system of claim 14 , wherein the at least one element is configured to move in response to a pressure difference between a stagnation pressure within the pneumatically actuated circuit breaker and a pressure of flow around the pneumatically actuated circuit breaker.

20. The rocket thrust vector control system of claim 14 , wherein the predetermined threshold is a flow velocity that will occur when the passive electrical turbine speed control fails.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Himmelmann Richard A

Classifications

• F02K9/566

  elements and safety devices, e.g. pressure relief valves · CPC title

• F04D15/0077

  Safety measures (F04D15/02 takes precedence) · CPC title

• F02C7/32

  Arrangement, mounting, or driving, of auxiliaries · CPC title

• F05D2270/021

  to prevent overspeed · CPC title

• F02K9/58 Primary

  Propellant feed valves · CPC title