1. An anisotropically conductive sheet formed by containing conductive particles exhibiting magnetism in a sheet base composed of an elastic polymeric substance in a state dispersed in a plane direction and oriented so as to align in a thickness-wise direction, wherein
a thickness of the sheet is 10 to 100 \u03bcm, a number average particle diameter of the conductive particles exhibiting magnetism is 5 to 50 \u03bcm, a ratio W1D of the thickness W1 to the number average particle diameter D of the conductive particles exhibiting magnetism is 1.1 to 10, a content of the conductive particles exhibiting magnetism is 10 to 40% in terms of a weight fraction, and the sheet is used for impedance measurement in a high-frequency region.
2. The anisotropically conductive sheet according to claim 1, wherein a conductive substance exhibiting no magnetism is contained in a uniformly dispersed state.
3. An anisotropically conductive sheet comprising, in a sheet base composed of an elastic polymeric substance, a plurality of conductive parts each containing conductive particles exhibiting magnetism at a high density and extending in a thickness-wise direction of the sheet base and an insulating part mutually insulating these conductive parts wherein
a thickness of the conductive parts is 10 to 100 \u03bcm, a number average particle diameter of the conductive particles exhibiting magnetism is 5 to 50 \u03bcm, a ratio W2D of the thickness W2 of the conductive part to the number average particle diameter D of the conductive particles exhibiting magnetism is 1.1 to 10, a content of the conductive particles exhibiting magnetism in the conductive part is 10 to 40% in terms of a weight fraction, and the sheet is used for impedance measurement in a high-frequency region.
4. The anisotropically conductive sheet according to claim 3, wherein a conductive substance exhibiting no magnetism is contained in the conductive parts and the insulating part in a uniformly dispersed state.
5. The anisotropically conductive sheet according to claim 3 or 4, wherein the conductive part, which is connected to a circuit to be measured of a board to be measured, and the conductive part, which is connected to a ground circuit of the board to be measured, in an impedance-measuring probe are separated from each other by the insulating part.
6. An impedance-measuring probe comprising the anisotropically conductive sheet according to any one of claims 1 to 5, wherein the probe is used in a high-frequency region.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A turbine blade having a shank portion and an airfoil portion with leading and trailing edges and a radially outer tip; an internal closed-loop cooling circuit within the airfoil portion including at least one radial outflow passage and at least one radial inflow passage connected by at least one respective tip turn at the radially outer end of the airfoil portion adjacent said radially outer tip, said at least one tip turn having a single elongated turbulence-enhancement device formed on an underside of, extending substantially across and engaged only with said radially outer tip, said device projecting into said tip turn.
2. The turbine blade of claim 1 wherein said single turbulence-enhancement device comprises a rib.
3. The turbine blade of claim 2 wherein said rib has a generally square cross-section.
4. The turbine blade of claim 2 wherein said rib has a generally rounded cross-section.
5. The turbine blade of claim 2 wherein said rib extends in a direction of cooling steam flow through the tip turn.
6. The turbine blade of claim 2 wherein said rib extends in a direction perpendicular to a direction of cooling steam flow through the tip turn.
7. The turbine blade of claim 2 wherein said rib extends in a direction diagonal to the direction of cooling steam flow through the tip turn.
8. The turbine blade of claim 2 wherein said rib is substantially chevron-shaped.
9. The turbine blade of claim 1 including a plurality of core support holes in said radially outer tip, each hole closed by a plug.
10. The turbine blade of claim 9 wherein said single turbulence-enhancement device comprises an elongated rib formed on an underside of said plug.
11. (canceled)
12. A turbine blade having a shank portion and an airfoil portion with leading and trailing edges and a radially outer tip; an internal closed-loop serpentine cooling circuit within the airfoil portion including plural radial outflow passages and plural radial inflow passages connected by plural respective tip turns at the radially outer end of the airfoil portion, and including a plurality of core support holes in said radially outer tip, each hole closed by a plug having not more than one elongated rib extending substantially across but engaged only with an underside of the plug, and projecting into a respective one of said tip turns.
13. The turbine blade of claim 12 wherein said rib has a generally square cross-section.
14. The turbine blade of claim 12 wherein said rib has a generally rounded cross-section.
15. The turbine blade of claim 12 wherein said rib extends in a direction of cooling steam flow through the tip turn.
16. The turbine blade of claim 12 wherein said rib extends in a direction perpendicular to a direction of cooling steam flow through the tip turn.
17. The turbine blade of claim 12 wherein said rib extends in a direction diagonal to the direction of cooling steam flow through the tip turn.
18. The turbine blade of claim 12 wherein said rib is substantially chevron-shaped.
19. (canceled)
20. A turbine blade having a shank portion and an airfoil portion with leading and trailing edges and a radially outer tip; an internal closed-loop serpentine cooling circuit within said airfoil portion including plural radial outflow passages and plural radial inflow passages connected by plural respective tip turns at said radially outer tip, and including a plurality of core support holes in said radially outer tip, each hole closed by a single plate covering a plurality of said core support holes having a plurality of ribs extending across and engaged only with an underside of said plate, but not more than one elongated rib on the underside of the plate projecting into a respective one of said tip turns.
21. A method of enhancing heat transfer in a respective, closed-loop cooling circuit formed within an airfoil portion of a gas turbine blade, said circuit including a plurality of radial outflow passages and a plurality of radial inflow passages connected by respective tip turns adjacent an airfoil tip having core support holes therein, the method comprising:
a) closing said core support holes with respective plugs; and
b) forming a single elongated rib on an underside of each plug, such that said rib extends across and engages only the underside of the plug and projects into said tip turn.
22. The method of claim 21 wherein said rib has a substantially square cross-section.
23. The method of claim 21 wherein said rib has a generally rounded cross-section.
24. The method of claim 21 wherein said rib extends in a direction diagonal to the direction of cooling steam flow through the tip turn.
25. The method of claim 21 wherein said rib extends in a direction of cooling steam flow through the tip turn.
26. The method of claim 21 wherein said rib extends in a direction perpendicular to a direction of cooling steam flow through the tip turn.
27. The method of claim 21 wherein said rib is substantially chevron-shaped.