Turbine thermal monitoring systems and methods
A gas turbine engine includes a core engine having a casing, a cowl disposed annularly around the casing such that a gap is formed between the casing and the cowl, and a thermal monitoring system having at least one camera positioned within the gap, wherein the at least one camera is configured to detect thermal radiation from at least one turbine component within the gap.
1. A gas turbine engine, comprising:
a core engine having a casing;
a cowl disposed annularly around the casing such that a gap is formed between the casing and the cowl; and
a thermal monitoring system having at least one camera positioned within the gap, wherein the at least one camera is configured to detect thermal radiation from at least one turbine component within the gap.
2. The gas turbine engine of claim 1 , wherein the at least one camera comprises an infrared (IR) camera configured to detect the thermal radiation from the at least one turbine component.
3. The gas turbine engine of claim 1 , wherein the at least one camera comprises a window, a lens, a mirror, an optical filter, and a sensor array, and wherein the at least one camera is positioned and oriented such that the window, the lens, the mirror, the optical filter, and the sensor array is pointed toward at least one component of interest of the at least one turbine component.
4. The gas turbine engine of claim 1 , wherein the at least one camera is configured to monitor the thermal radiation from the at least one turbine component during operation of the gas turbine engine.
5. The gas turbine engine of claim 1 , comprising:
a thermal management system having an engine controller, a cooling fluid supply source, and at least one sensor configured to detect a pressure of a cooling fluid adjacent or within the at least one camera, a temperature of the cooling fluid adjacent or within the at least one camera, or both;
wherein the engine controller is configured to receive data indicative of the pressure, the temperature, or both from the at least one sensor, and to control a flow of the cooling fluid from the cooling fluid supply source based on the data indicative of the pressure, the temperature, or both.
6. The gas turbine engine of claim 1 , wherein the thermal monitoring system comprises a controller communicatively coupled to the at least one camera, and wherein the controller is configured to coordinate data received from the at least one camera to generate a temperature map of the at least one turbine component.
7. The gas turbine engine of claim 6 , comprising a display communicatively coupled with the controller, wherein the controller is configured to output the temperature map to the display, wherein the temperature map utilizes two or more spectral bands correlated to the data.
8. The gas turbine engine of claim 1 , wherein the at least one camera comprises an additively manufactured camera case.
9. The gas turbine engine of claim 8 , wherein the additively manufactured camera case comprises at least one of the following:
a height between 0.2 inches to 2 inches;
a width between 0.2 inches to 2 inches; or
a length between 0.2 inches to 2 inches.
10. The gas turbine engine of claim 8 , comprising a flow path configured to direct a cooling fluid toward the additively manufactured camera case, wherein the cooling fluid comprises air, water, oil, fuel, or any combination thereof.
11. A method of monitoring a thermal distribution in a turbine system, comprising:
measuring, via one or more infrared (IR) cameras, thermal radiation from at least one under-cowl component disposed in a gap between a casing of the turbine system and a cowl of the turbine system;
converting the data indicative of the thermal radiation of the at least one under-cowl component into a surface temperature measurement of the at least one under-cowl component; and
generating, via a controller and based on the surface temperature measurement of the at least one under-cowl component, a temperature map of the at least one under-cowl component.
12. The method of claim 11 , wherein the one or more IR cameras comprises two or more IR cameras.
13. The method of claim 11 , comprising:
determining at least one component of interest from the at least one under-cowl component; and
positioning and orientating the one or more IR cameras such that a window, a lens, a mirror, an optical filter, and a sensor array of the one or more IR cameras is pointed toward the at least one component of interest.
14. The method of claim 11 , comprising:
correlating the surface temperature measurement into two or more spectral bands; and
generating the temperature map utilizing the two or more spectral bands.
15. The method of claim 11 , comprising measuring, via the one or more infrared (IR) cameras, the thermal radiation at a sampling rate of between 1 Hertz (Hz) and 60 Hz.
16. An in situ thermal monitoring system of a turbine engine, comprising:
two or more infrared (IR) cameras configured to detect thermal radiation of at least one turbine component disposed within a gap between a casing of the turbine engine and a cowl of the turbine engine; and
at least one processor, wherein the at least one processor is configured to receive data from the two or more IR cameras indicative of the thermal radiation of the at least one turbine component, to convert the data indicative of the thermal radiation into downstream data indicative of surface temperatures of the at least one turbine component, and to analyze the downstream data to generate a temperature map illustrating the surface temperatures of the at least one turbine component.
17. The in situ thermal monitoring system of claim 16 , wherein the at least one processor comprises:
a first processor of a first IR camera of the two or more IR cameras; and
a second processor of a second IR camera of the two or more IR cameras.
18. The in situ thermal monitoring system of claim 16 , wherein a first IR camera of the two or more IR cameras comprises a camera case configured to:
hold an IR window, an IR lens, an IR optical filter, and an IR camera;
protect the first IR camera from thermal exposure; and
receive a cooling fluid and protect components of the first IR camera from an environment.
19. The in situ thermal monitoring system of claim 16 , wherein a first IR camera case of the two or more IR cameras comprises at least one of the following:
a height between 0.2 inches and 2 inches;
a width between 0.2 inches and 2 inches; or
a length between 0.2 inches and 2 inches.
20. The in situ thermal monitoring system of claim 16 , comprising a display communicatively coupled with the at least one processor, wherein the at least one processor is configured to output the temperature map on the display.