1. A turbine stator nozzle comprising:
a row of vanes joined at opposite ends to outer and inner bands;
each of said vanes having a concave pressure side and circumferentially opposite, convex suction side extending radially in span between said bands and axially in chord between opposite leading and trailing edges;
said inner band being inclined outwardly between said leading and trailing edges and said outer band being correspondingly inclined more than said inner band, with said vanes having camber for turning combustion gases between said leading and trailing edges, and also having an acute twist angle for imparting swirl in said combustion gases discharged at said trailing edges; and
said trailing edges being tilted forwardly from said inner band with oblique lean at said outer band to narrow said vanes in axial width at said outer band and correspond generally in axial width of said vanes at said inner band.
2. A nozzle according to claim 1 wherein said inclined bands have a divergence ratio defined by the difference in radial span between said leading and trailing edges at said outer band divided by the average radial span between said bands from said leading edge to said trailing edge, with said ratio being less than about 0.4.
3. A nozzle according to claim 2 wherein said vane leading edges are also tilted forward from said inner band, and said trailing edge tilt conforms with said leading edge tilt.
4. A nozzle according to claim 3 wherein said inner band terminates closely adjacent to said vane trailing edges, and said outer band terminates with a spacing aft from said trailing edges vertically aligned with said inner band.
5. A nozzle according to claim 3 wherein said vane trailing edges are inclined at a common tilt angle from said inner band to said outer band.
6. A turbofan engine comprising:
a fan driven by a low pressure turbine, and a compressor following said fan and driven by a high pressure turbine preceding said low pressure turbine in counterrotation therewith;
said low pressure turbine including a first stage stator nozzle including a row of vanes joined at opposite ends to radially outwardly inclined outer and inner bands;
each of said vanes having arcuate camber between leading and trailing edges thereof, and an acute twist angle for imparting swirl in combustion gases channeled between said high pressure turbine and said low pressure turbine; and
said trailing edges being tilted forward from said inner band with oblique lean at said outer band.
7. An engine according to claim 6 wherein said inclined bands have a divergence ratio defined by the difference in radial span between said leading and trailing edges at said outer band divided by the average radial span between said bands from said leading edge to said trailing edge, with said ratio being less than about 0.4.
8. An engine according to claim 7 wherein said vanes are narrow in axial width between said leading and trailing edges with said width being less than the radial length between said outer and inner bands.
9. An engine according to claim 8 further comprising a transition duct having a row of fairings disposed axially between said high pressure turbine and said first stage nozzle, and wherein said high pressure turbine includes two stages of rotor blades therein.
10. An engine according to claim 8 wherein said first stage nozzle is disposed directly between corresponding stages of said rotor blades in said high pressure turbine and said low pressure turbine, and said high pressure turbine includes a single stage of said rotor blades therein.
11. A turbine stator nozzle comprising:
a row of vanes joined at opposite ends to outer and inner bands;
each of said vanes having a concave pressure side and circumferentially opposite, convex suction side extending radially in span between said bands and axially in chord between opposite leading and trailing edges;
said bands being inclined outwardly between said leading and trailing edges, with said vanes having camber for turning combustion gases between said leading and trailing edges, and also having an acute twist angle for imparting swirl in said combustion gases discharged at said trailing edges; and
said trailing edges being inclined forwardly from said inner band at an acute tilt angle to effect oblique lean at said outer band with greater spacing aft of said trailing edges at said outer band than at said inner band.
12. A nozzle according to claim 11 wherein said outer band is inclined more than said inner band.
13. A nozzle according to claim 12 wherein said vanes are narrow in axial width between said leading and trailing edges with said width being less than the radial length between said outer and inner bands.
14. A nozzle according to claim 13 wherein said vanes are correspondingly narrow at both said outer and inner bands.
15. A nozzle according to claim 13 wherein said vane leading edges are also tilted forward from said inner band, and said trailing edge tilt conforms with said leading edge tilt.
16. A nozzle according to claim 13 wherein said inclined bands have a divergence ratio defined by the difference in radial span between said leading and trailing edges at said outer band divided by the average radial span between said bands from said leading edge to said trailing edge, with said ratio being less than about 0.4.
17. A nozzle according to claim 16 wherein said divergence ratio is about 0.2.
18. A nozzle according to claim 13 wherein said inner band terminates closely adjacent to said vane trailing edges, and said outer band terminates with a spacing aft from said trailing edges vertically aligned with said inner band.
19. A nozzle according to claim 18 wherein said outer and inner bands commence forwardly from said vanes with a spacing less than about the nominal width of said vanes.
20. A nozzle according to claim 18 wherein said outer and inner bands commence forwardly from said vanes with a spacing greater than about the nominal width of said vanes.
21. A nozzle according to claim 13 in combination with a high pressure turbine disposed upstream from said vanes for channeling said combustion gases thereto, and a multistage low pressure turbine commencing with said vanes for extracting energy from said combustion gases.
22. A combination according to claim 21 wherein said high pressure turbine includes rotor blades joined to a first rotor, and said low pressure turbine includes rotor blades joined to a second rotor, with said blades being oppositely oriented for counterrotating said first and second rotors.
23. A combination according to claim 22 further comprising a transition duct having a row of fairings disposed axially between said high pressure turbine and said turbine nozzle.
24. A combination according to claim 23 wherein said transition duct includes radially outwardly inclined outer and inner platforms supporting said fairings, with said outer band being inclined radially outwardly from said outer platform, and said inner band being inclined radially outwardly from said inner platform.
25. A combination according to claim 24 wherein said high pressure turbine includes two stages of rotor blades therein.
26. A combination according to claim 22 where said turbine nozzle is disposed directly between corresponding stages of said rotor blades in said high pressure turbine and said low pressure turbine.
27. A combination according to claim 26 wherein said outer and inner bands commence forwardly from said vanes with a spacing equal to about the average radial span of said vanes.
28. A combination according to claim 26 wherein said high pressure turbine includes a single stage of said rotor blades therein.
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 body-insertable device, configured to be introduced into a desired part in a body for injecting a liquid medicine stored in a casing into the desired part, the body-insertable device comprising:
a projecting portion which projects an injection needle injecting the liquid medicine toward the desired part, the injection needle having a plurality of angle detection markers each having a predetermined width in a longitudinal direction of the injection needle;
an imaging unit which images an image including the injection needle projected from the casing;
an angle detecting unit which detects the angle detection markers from the image, and calculates a puncture angle, formed between a biological tissue surface in the desired part and the injection needle, based on a result of the detection; and
a control unit which controls a puncture depth of the injection needle from a biological tissue surface in the desired part based on the calculated puncture angle of the injection needle and the plurality of angle detection markers.
2. The body-insertable device according to claim 1, wherein
the angle detection markers are color markers each indicating a distance from a tip of the injection needle, and
the angle detecting unit detects, from the image, the color markers near a puncturing portion of the injection needle which punctures the desired part from the plurality of color markers and calculates the puncture angle of the injection needle based on a figure of the color markers near the puncturing portion.
3. The body-insertable device according to claim 1, further comprising a circular ring marker which is slidably provided at a tip of the injection needle and changes its angle with respect to the injection needle corresponding to the biological tissue surface in the desired part punctured by the injection needle, wherein
the imaging unit fixes a first angle formed between a light receiving surface thereof and the injection needle and images the image including the injection needle projected from the casing and the ring marker, and
the angle detecting unit calculates a second angle formed between a plane formed by the ring marker and the light receiving surface according to a shape of the ring marker detected according to the image, and calculates the puncture angle of the injection needle based on the first angle and the second angle.
4. A liquid medicine injection method comprising:
introducing a body-insertable device having a liquid medicine and an injection needle injecting the liquid medicine in a casing into a desired part in a body;
projecting the injection needle from the body-insertable device to the desired part, the injection needle having a plurality of angle detection markers each having a predetermined width in a longitudinal direction of the injection needle;
detecting the angle detection markers and calculating a puncture angle formed between a biological tissue surface in the desired part and the injection needle based on a result of the detection; and
controlling a puncture depth of the injection needle from the biological tissue surface based on the calculated puncture angle and the plurality of angle detection markers on the injection needle.
5. The liquid medicine injection method according to claim 4, wherein the detecting includes detecting the angle by imaging an image showing a position relation between the biological tissue surface and the injection needle.
6. The liquid medicine injection method according to claim 5, wherein the controlling includes performing a predetermined image processing on the image showing the position relation and controlling a puncture depth of the injection needle based on the result of the image processing.