Sensor

Abstract

A sensor which uses a detection element such as a surface acoustic wave element, and includes a flow passage for a specimen is provided. A sensor includes a substrate; a detection element located on the substrate and having a detection portion which detects an object to be detected contained in a specimen, in an upper surface thereof; and a flow passage structure located on the substrate and covering the detection portion with a space. The flow passage structure has an inlet for the specimen, a flow passage continuing from the inlet, and a space which continues from an end portion of the flow passage closer to the detection element and is located above the detection portion, and a bottom surface of the flow passage has, on the end portion of the flow passage closer to the detection element, a notched portion whose width gradually decreases toward an upstream of the flow passage.

What is claimed is: 
     
         1 . A gas turbine engine, comprising:
 an inner shaft extending axially along the gas turbine engine;   a plurality of disks extending radially inwardly and toward the inner shaft;   at least one hole in at least one of the plurality of disks; and   an obstruction positioned between the inner shaft and an end of the disk having the at least one hole, such that a bore flow that flows along an axial length of the inner shaft is obstructed from flowing along the shaft by the obstruction, and forced to flow radially outward from the obstruction, through the at least one hole, and radially inward toward the inner shaft.   
     
     
         2 . The gas turbine engine of  claim 1 , further comprising a cone shaft aft of the plurality of disks, and a cavity formed in part by an external portion of the cone shaft, wherein cooled cooling air (CCA) is received aft of a diffuser, caused to flow forward, opposite an aft end of the gas turbine, and into the cavity, and split within the cavity such that some of the CCA is caused to flow forward in the cavity to exit at an aft face of the gas turbine engine. 
     
     
         3 . The gas turbine engine of  claim 2 , wherein, at the split within the cavity, some of the CCA is caused to flow down the cone shaft toward the aft end of the gas turbine and along an outer surface of a C-T shaft and to a C-T bolted joint of the gas turbine engine. 
     
     
         4 . The gas turbine engine of  claim 3 , further comprising a hole in another of the plurality of disks, wherein a second cavity is formed in part by the another of the plurality of disks, an inner surface of the C-T shaft, and the inner shaft, such that some of the bore flow obstructed from flowing along the shaft flows through the hole in the another of the plurality of disks, into the second cavity, and rejoins with the bore flow aft of the obstruction. 
     
     
         5 . The gas turbine engine of  claim 4 , wherein the external portion of the cone shaft is one surface of the cone shaft, and the second cavity is formed in part by a second surface of the cone shaft that is opposite the one surface of the cone shaft. 
     
     
         6 . The gas turbine engine of  claim 1 , wherein the bore flow that is forced to flow radially outward flows along a first surface of the at least one of the plurality of disks, and flows radially inward along a second surface, opposite the first surface, of the at least one of the plurality of disks. 
     
     
         7 . The gas turbine engine of  claim 1 , wherein the obstruction is coupled to an outer surface of the inner shaft and the end of the disk having the at least one hole. 
     
     
         8 . A method of assembling a gas turbine engine, comprising:
 positioning an inner shaft to extend along a rotational axis of the gas turbine engine;   positioning disks to extend radially inward toward the inner shaft;   forming a hole in a first of the disks; and   positioning an obstruction between the inner shaft and an end of the first disk, such that a bore flow that flows along the rotational axis and along the inner shaft is obstructed from flowing along the shaft by the obstruction, and forced to flow radially outward from the obstruction, through the hole, and radially inward toward the inner shaft.   
     
     
         9 . The method of  claim 8 , further comprising positioning a cone shaft aft of the disks to form a cavity in part by an external portion of the cone shaft, wherein cooled cooling air (CCA) is received aft of a diffuser, caused to flow forward, opposite an aft end of the gas turbine, into the cavity, and split within the cavity such that some of the CCA is caused to flow forward in the cavity to exit at an aft face of the gas turbine engine. 
     
     
         10 . The method of  claim 9 , wherein, at the split within the cavity, some of the CCA is caused to flow down the cone shaft toward the aft end of the gas turbine and along an outer surface of a C-T shaft and to a C-T bolted joint of the gas turbine engine. 
     
     
         11 . The method of  claim 10 , further comprising forming another hole in a second of the disks, wherein a second cavity is formed in part by the second of the disks, an inner surface of the C-T shaft, and the inner shaft, such that some of the bore flow obstructed from flowing along the shaft flows through the hole in the second disk, into the second cavity, and rejoins with the bore flow aft of the obstruction. 
     
     
         12 . The method of  claim 11 , wherein the external portion of the cone shaft is one surface of the cone shaft, and the second cavity is formed in part by a second surface of the cone shaft that is opposite the one surface of the cone shaft. 
     
     
         13 . The method of  claim 8 , wherein the bore flow that is forced to flow radially outward flows along a first surface of the first disk, and flows radially inward along a second surface, opposite the first surface, of the first disk. 
     
     
         14 . The method of  claim 8 , further comprising coupling the obstruction to an outer surface of the inner shaft and the end of the first disk. 
     
     
         15 . A method of cooling a gas turbine engine, comprising:
 directing a bore flow to flow along a rotational axis of an inner shaft of the gas turbine engine and to an obstruction along the inner shaft that obstructs the bore flow from flowing along the shaft, wherein the bore flow is forced radially outward from the obstruction, through a hole in a first disk, and radially inward toward the inner shaft, and wherein the disk extends radially inward toward the inner shaft.   
     
     
         16 . The method of  claim 15 , further comprising receiving cooled cooling air (CCA) aft of a diffuser, flowing the CCA in a forward direction of the gas turbine engine that is opposite an aft end of the gas turbine, into a cavity, and splitting the CCA within the cavity such that some of the CCA is caused to flow forward in the cavity to exit at an aft face of the gas turbine engine, wherein the cavity is formed in part by an external portion of the cone shaft. 
     
     
         17 . The method of  claim 16 , wherein, at the split within the cavity, the method further comprises flowing some of the CCA down the cone shaft toward the aft end of the gas turbine and along an outer surface of a C-T shaft and to a C-T bolted joint of the gas turbine engine. 
     
     
         18 . The method of  claim 17 , further comprising flowing some of the bore flow that is obstructed through a hole in a second disk, into a second cavity that is formed in part by the second of the disks, an inner surface of the C-T shaft, and the inner shaft, and rejoining with the bore flow aft of the obstruction. 
     
     
         19 . The method of  claim 18 , wherein the external portion of the cone shaft is one surface of the cone shaft, and the second cavity is formed in part by a second surface of the cone shaft that is opposite the one surface of the cone shaft. 
     
     
         20 . The method of  claim 15 , wherein the bore flow that is forced to flow radially outward flows along a first surface of the first disk, and flows radially inward along a second surface, opposite the first surface, of the first disk.