System and method for cooling discharge flow

Patent metadata

Field	Value
Publication number	US-10145269-B2
Application number	US-201615060089-A
Country	US
Kind code	B2
Filing date	Mar 3, 2016
Priority date	Mar 4, 2015
Publication date	Dec 4, 2018
Grant date	Dec 4, 2018

Abstract

A system includes a probe. The probe includes a sensing component configured to sense a parameter of a turbomachine. The probe also includes an inlet configured to receive a cooling inflow. The probe also includes a cooling passage configured to receive the cooling inflow from the inlet. The cooling passage is disposed along at least a portion of the probe, and the cooling inflow absorbs heat from the probe. The probe also includes an outlet coupled to the cooling passage and configured to receive an outflow from the cooling passage. The outflow includes at least a portion of the cooling inflow. The system also includes an ejector coupled to the outlet.

First claim

The invention claimed is:

1. A system comprising:
a probe, comprising:
a sensing component configured to sense a parameter of a turbomachine;
a body comprising an end portion coupled to the sensing component;
an inlet configured to receive a cooling inflow;
a shell coupled to the inlet, wherein the shell defines a cooling passage configured to receive the cooling inflow from the inlet, wherein the cooling passage is disposed longitudinally along at least a portion of the body of the probe, and the cooling inflow is configured to absorb heat from the probe; and
an outlet coupled to the shell, wherein the outlet is configured to receive an outflow from the cooling passage, wherein the outflow comprises at least a portion of the cooling inflow; and

an ejector coupled to the outlet, wherein the ejector comprises:
an interior;
an opening fluidly coupled to the interior, wherein the opening is configured to receive a coolant;
a nozzle coupled to the outlet, wherein the nozzle is configured to constrict the outflow from the outlet and to deliver the outflow to the interior; and
a mixing portion configured to mix the outflow and the coolant to provide a discharge flow.

2. The system of claim 1 , wherein the probe comprises a lambda probe and the parameter comprises an oxygen content of a working flow of the turbomachine, and the turbomachine comprises a gas turbine engine.

3. The system of claim 1 , wherein the probe comprises a temperature probe and the parameter comprises a temperature of a portion of the turbomachine.

4. The system of claim 1 , wherein the probe comprises a flow-sensing probe and the parameter comprises a flow rate of a working flow of the turbomachine.

5. The system of claim 1 , wherein the cooling inflow comprises air, carbon dioxide, nitrogen, or any combination thereof.

6. The system of claim 1 , comprising the turbomachine, wherein the turbomachine comprises a gas turbine engine, and the cooling inflow comprises a recirculated exhaust gas of the gas turbine engine.

7. The system of claim 6 , wherein the gas turbine engine comprises a turbine combustor, a turbine configured to be driven by combustion gases from the turbine combustor and configured to output an exhaust gas, and an exhaust gas compressor configured to be driven by the turbine, wherein the exhaust gas compressor is configured to compress and to route the exhaust gas to the turbine combustor.

8. The system of claim 7 , wherein the gas turbine engine is a stoichiometric exhaust gas recirculation (SEGR) gas turbine engine.

9. The system of claim 8 , comprising an exhaust gas extraction system coupled to the gas turbine engine, and a hydrocarbon production system coupled to the exhaust gas extraction system.

10. The system of claim 1 , wherein the coolant comprises ambient air, wherein a temperature of the ambient air is less than 40° C.

11. The system of claim 1 , wherein the sensing component of the probe is disposed at an axial end of the probe, and the cooling passage is configured to direct the cooling inflow along an axis of the probe towards the axial end.

12. The system of claim 1 , wherein the ejector comprises a converging section, a throat disposed downstream of the converging section, and a diverging section disposed downstream of the throat, wherein the nozzle is disposed upstream of the converging section, and the mixing portion is disposed in the converging section.

13. A system comprising:
a probe, comprising:
a sensing component configured to sense a parameter of a gas turbine engine;
a body comprising an end portion coupled to the sensing component;
an inlet configured to receive a cooling inflow;
a shell coupled to the inlet, wherein the shell defines a cooling passage configured to receive the cooling inflow from the inlet, wherein the cooling passage is disposed longitudinally along at least a portion of the body of the probe, and the cooling inflow is configured to absorb heat from the probe to form a heated outflow; and
an outlet coupled to the shell, wherein the outlet is configured to receive the heated outflow from the cooling passage, wherein a temperature of the heated outflow at the outlet is greater than 80° C.; and

an ejector coupled to the outlet, wherein the ejector comprises:
an interior;
an opening fluidly coupled to the interior, wherein the opening is configured to receive a coolant;
a nozzle coupled to the outlet, wherein the nozzle is configured to constrict the heated outflow from the outlet and to deliver the heated outflow to the interior; and
a mixing portion configured to mix the heated outflow and the coolant to provide a discharge flow, wherein a temperature of the discharge flow is less than 80° C.

14. The system of claim 13 , wherein the probe comprises a lambda probe and the parameter comprises an oxygen content of a working flow of the gas turbine engine.

15. The system of claim 13 , wherein the probe comprises a temperature probe and the parameter comprises a temperature of a portion of the gas turbine engine.

16. The system of claim 13 , wherein the probe comprises a flow-sensing probe and the parameter comprises a flow rate of a working flow of the gas turbine engine.

17. The system of claim 13 , wherein the cooling inflow comprises air, carbon dioxide, nitrogen, or any combination thereof.

18. The system of claim 13 , wherein the coolant comprises ambient air, and a temperature of the ambient air is less than 40° C.

19. The system of claim 13 , wherein the nozzle comprises a nozzle outlet adjacent to the interior, the nozzle outlet comprises a first diameter, the outlet of the probe comprises a second diameter, and the first diameter is greater than the second diameter.

20. The system of claim 13 , wherein the ejector comprises a door coupled to the opening, wherein the door is configured to control a flow rate of the coolant through the opening.

21. A method comprising:
supplying a cooling inflow to a cooling passage disposed longitudinally along at least a portion of a body of a probe configured to sense a parameter of a gas turbine engine, wherein the cooling inflow routed longitudinally along at least the portion of the body and the cooling inflow is configured to absorb heat from the probe to form a heated outflow;
directing the heated outflow from the probe to an ejector, wherein the ejector comprises a nozzle coupled to an outlet of the probe;
constricting the heated outflow through the nozzle into an interior of the ejector to draw a coolant into the interior of the ejector via an opening;
mixing the heated outflow and the coolant to form a discharge flow in a mixing portion of the ejector; and
directing the discharge flow to an ejector outlet of the ejector, wherein a temperature of the discharge flow is less than 80° C.

22. The method of claim 21 , comprising sensing a parameter of a working flow of the gas turbine engine, wherein the parameter comprises an oxygen content, a temperature, a flow rate, or any combination thereof, of the working flow.

23. The method of claim 21 , wherein supplying the cooling inflow to the probe comprises supplying air, carbon dioxide, nitrogen, or any combination thereof, to the probe.

24. The method of claim 21 , wherein constricting the heated outflow through the nozzle to draw the coolant into the interior of the ejector comprises constricting the heated outflow through the nozzle to draw ambient air into the interior of the eject

Assignees

• Gen Electric
• Exxonmobil Upstream Res Co

Inventors

• Pakkala Srinivas

Classifications

• F23N2241/20

  Gas turbines · CPC title

• F23N2225/30

  measuring lambda · CPC title

• F23N5/006

  the detector being sensitive to oxygen · CPC title

• F23N5/022

  using electronic means (F23N5/04 - F23N5/14 take precedence) · CPC title

• F23N2900/05005

  Mounting arrangements for sensing, detecting or measuring devices · CPC title