Apparatus and method for transmitting radiation to a rotating component
An apparatus and method for radiation measurement are used to determine clearance of a rotating gas turbine component. The apparatus includes a probe body on a stationary component outward of the rotating component and a pair of sensor assemblies coupled to the probe body. Each sensor assembly includes a plurality of prisms coupled to the probe body Each prism of the plurality of prisms has a distinct angular orientation to direct radiation from the focusing lens to the rotating component surface off-axis with respect to an axis of the respective radiation source of the pair of radiation sources and with less directional variation than radiation from the respective radiation source.
1. A probe assembly for transmitting radiation from a pair of radiation sources to a rotating component surface, the probe assembly comprising:
a probe body on a stationary component;
a pair of sensor assemblies coupled to the probe body, each sensor assembly including:
a plurality of prisms coupled to the probe body, each prism of the plurality of prisms having a distinct angular orientation to direct radiation from a respective radiation source to the rotating component surface off-axis with respect to an axis of the respective radiation source of the pair of radiation sources and with less directional variation than radiation from the respective radiation source.
2. The probe assembly of claim 1 , wherein each sensor assembly further includes a focusing lens coupled to the probe body and optically coupled between a respective radiation source of the pair of radiation sources and the plurality of prisms.
3. The probe assembly of claim 2 , wherein the focusing lens, in each of the pair of sensor assemblies, includes a set of axially opposed rounded edges.
4. The probe assembly of claim 2 , wherein each of the pair of radiation sources includes an optical fiber and wherein the focusing lens, of the respective sensor assembly, is coupled to an output end of the respective optical fiber.
5. The probe assembly of claim 1 , further comprising a purge fluid passage within the probe body, wherein the purge fluid passage fluidly couples a purge fluid source to the plurality of prisms in each of the pair of sensor assemblies.
6. The probe assembly of claim 1 , wherein the plurality of prisms, in each of the pair of sensor assemblies, is configured to direct the radiation from the respective radiation source along a pathway that is approximately twenty degrees from a centerline axis of the probe body.
7. The probe assembly of claim 1 , wherein each of the plurality of prisms, in each of the pair of sensor assemblies, is a right-angle prism.
8. The probe assembly of claim 1 , wherein the rotating component surface is a surface of a rotating blade of a turbomachine; and the probe body is coupled to a casing of the turbomachine positioned radially outward from the rotating blade.
9. The probe assembly of claim 1 , further comprising at least two light pipes, each light pipe coupled to the probe body and physically decoupled from each plurality of prisms, wherein each light pipe is positioned to detect the radiation after the radiation is deflected from the rotating component surface.
10. An apparatus for measuring a clearance within a turbomachine, the apparatus comprising:
a probe assembly on a casing of a turbomachine, the probe assembly including:
a probe body mounted to the casing;
a pair of sensor assemblies coupled to the probe body, each sensor assembly including:
a plurality of prisms coupled to the probe body, each prism of the plurality of prisms having a distinct angular orientation to direct radiation from a respective radiation source to a rotating component surface off-axis with respect to an axis of the respective radiation source and with less directional variation than radiation from the respective radiation source;
a detector for receiving radiation deflected from the rotating component surface; and
a controller coupled to the detector, wherein the controller calculates the clearance as a distance between the probe assembly and the rotating component surface based on an elapsed time between detection of deflected radiation from a first radiation source and detection of deflected radiation from a second radiation source.
11. The apparatus of claim 10 , wherein each sensor assembly further includes a focusing lens coupled to the probe body and optically coupled between a respective radiation source of the pair of radiation sources and a respective plurality of prisms.
12. The apparatus of claim 11 , wherein the focusing lens, in each of the pair of sensor assemblies, includes a set of axially opposed rounded edges, each of the pair of radiation sources includes an optical fiber, and the focusing lens, of the respective sensor assembly, is coupled to an output end of the respective optical fiber.
13. The apparatus of claim 10 , further comprising a purge fluid passage within the probe body, wherein the purge fluid passage fluidly couples a purge fluid source to the plurality of prisms in each of the pair of sensor assemblies.
14. The apparatus of claim 10 , wherein the rotating component surface is a surface of a rotating blade of the turbomachine.
15. A method for transmitting radiation to a surface of a rotating component, the method comprising:
transmitting radiation from a pair of radiation sources through at least two sensor assemblies disposed in a probe body on a stationary component radially spaced from the rotating component, wherein each sensor assembly includes:
a plurality of prisms coupled to the probe body, each prism having a distinct angular orientation such that the plurality of prisms directs radiation from the respective radiation source to the surface of the rotating component off-axis with respect to an axis of the respective radiation source and with less directional variation than radiation from a respective radiation source of the pair of radiation sources;
measuring one of an elapsed time or rotation distance between detection of deflected radiation from a first radiation source from the surface of the rotating component and detection of deflected radiation from a second radiation source from the surface of the rotating component; and
calculating, via a controller, a clearance distance between the stationary component and the rotating component based on the elapsed time or the rotation distance.
16. The method of claim 15 , further comprising passing purge fluid from a passage within the probe body over the plurality of prisms, in each of the pair of sensor assemblies, to remove contaminants therefrom.
17. The method of claim 15 , wherein each sensor assembly of the at least two sensor assemblies further includes a focusing lens coupled to the probe body radially outward of the plurality of prisms; and wherein transmitting radiation from the pair of radiation sources through the at least two sensor assemblies further comprises directing the radiation through the respective focusing lens of each respective sensor assembly prior to directing the radiation through the plurality of prisms; and wherein directing the radiation through the plurality of prisms causes the radiation to be oriented along a pathway that is approximately twenty degrees from a centerline axis of the probe body.
18. The method of claim 15 , wherein the rotating component includes a blade of a turbomachine; and wherein the stationary component includes a casing of the turbomachine.
19. The method of claim 15 , further comprising collecting radiation deflected from the surface of the rotating component in a pair of light pipes coupled to the probe body, wherein the pair of light pipes are physically decoupled from the at least two sensor assemblies.
20. The method of claim 15 , wherein each radiation source of the pair of radiation sources includes an optical fiber, and further comprising, for each sensor assembly, coupling a focusing lens to an output end of the optical fiber such that the radiation is directed through the focusing lens prior to be directed through the plurality of prisms.