System and method for cooling discharge flow

Patent metadata

Field	Value
Publication number	US-10968781-B2
Application number	US-201816208160-A
Country	US
Kind code	B2
Filing date	Dec 3, 2018
Priority date	Mar 4, 2015
Publication date	Apr 6, 2021
Grant date	Apr 6, 2021

Abstract

A system includes a probe disposed through one or more walls of a turbomachine. The probe includes a sensing component configured to sense a parameter of the turbomachine. The probe also includes a body coupled to the sensing component, an inlet configured to receive a cooling inflow, a shell that defines a cooling passage, and an outlet. The sensing component is disposed on a warm side of the one or more walls. The inlet and the outlet are disposed on a cool side of the one or more walls. The cooling passage directs the cooling inflow toward the sensing component and toward the outlet. The outlet is configured to receive an outflow from the cooling passage, wherein the outflow includes at least a portion of the cooling inflow.

First claim

The invention claimed is:

1. A system comprising:
a first probe disposed through one or more walls of a turbomachine, comprising:
a sensing component configured to sense a parameter of a turbomachine, wherein the sensing component is disposed on a warm side of the one or more walls;
a first body coupled to the sensing component;
a first inlet configured to receive a first cooling inflow, wherein the first inlet is disposed on a cool side of the one or more walls;
a first shell coupled to the first inlet, wherein the first shell defines a first cooling passage that extends through the one or more walls of the turbomachine, wherein the first cooling passage is configured to direct the first cooling inflow from the first inlet toward the sensing component of the first probe and toward a first outlet coupled to the first shell; and
the first outlet, wherein the first outlet is disposed on the cool side of the one or more walls, and the first outlet is configured to receive a first outflow from the first cooling passage, wherein the first outflow comprises at least a first portion of the first cooling inflow; and

an ejector coupled to the first outlet, wherein the ejector is configured to mix a coolant with the first outflow to reduce a temperature and a velocity of the first outflow.

2. The system of claim 1 , wherein the first probe comprises a lambda probe, a temperature probe, a flow-sensing probe, or a composition.

3. The system of claim 1 , wherein the first body of the first probe comprises a processor, a memory, or any combination thereof.

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

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

6. The system of claim 1 , wherein the turbomachine comprises a gas turbine engine, and the one or more walls comprise a compressor discharge casing of the gas turbine engine.

7. The system of claim 1 , wherein the turbomachine comprises a gas turbine engine, and the one or more walls comprise a combustor liner of the gas turbine engine, a flow sleeve of the gas turbine engine, or any combination thereof.

8. The system of claim 1 , wherein the cool side of the one or more walls is disposed in a first environment with a first temperature less than 40° C., and the warm side of the one or more walls is disposed in a second environment with a second temperature greater than 200° C. during operation of the turbomachine.

9. The system of claim 8 , wherein the first cooling passage is closed from the second environment, and the first outflow consists essentially of the first cooling inflow.

10. The system of claim 1 , comprising a second probe, comprising:
a second body;
a second inlet configured to receive a second cooling inflow from an opening coupled to the cooling passage of the first probe, wherein the opening is disposed between the first inlet and the first outlet, and the second cooling inflow comprises a second portion of the first cooling inflow;
a second shell coupled to the second inlet, wherein the second shell defines a second cooling passage configured to receive the second cooling flow from the second inlet, and the second cooling flow is configured to absorb heat from the second probe; and
a second outlet coupled to the second shell, wherein the second outlet is configured to receive a second outflow from the second cooling passage, wherein the second outflow comprises the second cooling flow.

11. A gas turbine system comprising:
a probe disposed through a wall of the gas turbine system, comprising:
a sensing component configured to sense a parameter of working fluid of a gas turbine engine, wherein the sensing component is disposed on a warm side of the wall, wherein the warm side of the wall is disposed in an environment with a second temperature greater than 200° C. during operation of the gas turbine system;
a body coupled to the sensing component;
an inlet configured to receive a cooling inflow, wherein the inlet is disposed on a cool side of the wall with a first temperature less than 40° C.;
a shell coupled to the inlet, wherein the shell defines a cooling passage that extends through the one or more walls of the turbomachine, wherein the cooling passage is configured to direct the cooling inflow from the inlet toward the sensing component along at least a length of the probe and toward an outlet coupled to the shell, wherein the cooling inflow is configured to absorb heat from the probe to form a heated outflow; and
the outlet, wherein the outlet is disposed on the cool side of the wall, and the outlet is configured to receive the heated outflow from the cooling passage; and

an ejector coupled to the outlet, wherein the ejector is configured to mix a coolant with the heated outflow to reduce a temperature and a velocity of the heated outflow.

12. The gas turbine system of claim 11 , wherein the probe comprises a lambda probe, a temperature probe, a flow-sensing probe, or a composition probe.

13. The gas turbine system of claim 11 , wherein the wall comprises a casing of the gas turbine system, a flow sleeve of the gas turbine system, or a combustor liner of the gas turbine system, or any combination thereof.

14. The gas turbine system of claim 11 , wherein the working fluid comprises combustion gases of the gas turbine system, a recirculated exhaust gas of the gas turbine system, or any combination thereof.

15. A method comprising:
supplying a first cooling inflow to a first inlet of a first probe disposed on a cool side of a wall of a gas turbine system;
directing the first cooling inflow through a first cooling passage disposed longitudinally along at least a first length of a first body of the first probe toward an axial end of the first probe disposed on a warm side of the wall, wherein the first probe is configured to sense a first parameter of the gas turbine system, wherein the first cooling inflow is configured to absorb heat from the first probe to form a first heated outflow;
directing the first heated outflow from the axial end of the first probe to a first outlet, wherein the first outlet is disposed on the cool side of the wall of the gas turbine system;
directing the first heated outflow to a second inlet of a second probe of the gas turbine system; and
directing the first heated inflow through a second cooling passage disposed longitudinally along at least a second length of a second body of the second probe, wherein the second probe is configured to sense a second parameter of the gas turbine system, wherein the first heated outflow is configured to absorb heat from the second probe to form a second heated outflow.

16. The method of claim 15 , comprising sensing the first parameter of the gas turbine system, wherein the first parameter comprises an oxygen content, a temperature, a flow rate, or any combination thereof.

17. The method of claim 15 , wherein supplying the first cooling inflow to the first probe comprises supplying air, carbon dioxide, nitrogen, recirculated exhaust gas, or any combination thereof.

Assignees

• Gen Electric
• Exxonmobil Upstream Res Co

Inventors

• Pakkala Srinivas

Classifications

• F23N5/003 Primary

  using detectors sensitive to combustion gas properties (F23N5/02, F23N5/18 - F23N5/26 take precedence) · 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

• F23N5/006

  the detector being sensitive to oxygen · CPC title

• F23N2241/20

  Gas turbines · CPC title