1. A mote system comprising:
an antenna signal detection unit; and
a directional antenna system operably coupled with said antenna signal detection unit, said directional antenna system including:
an antenna control unit configured to direct a movement of a field of regard of a directional antenna such that the field of regard of the directional antenna will likely operably align with a beam of an other directional antenna.
2. The mote system of claim 1, wherein said directional antenna system operably coupled with said antenna signal detection unit further comprises:
a beam-forming antenna system.
3. The mote system of claim 1, wherein said directional antenna system operably coupled with said antenna signal detection unit further comprises:
a beam-steering antenna system.
4. (canceled)
5. (canceled)
6. The mote system of claim 1, wherein said directional antenna system operably coupled with said antenna signal detection unit further comprises:
one or more electromagnetic reflectors of one or more shapes corresponding to one or more selected antenna patterns.
7. The mote system of claim 1, wherein said directional antenna system operably coupled with said antenna signal detection unit further comprises:
an adaptive-antenna system.
8. (canceled)
9. (canceled)
10. (canceled)
11. The mote system of claim 1, wherein said directional antenna system operably coupled with said antenna signal detection unit further comprises:
an array antenna.
12. (canceled)
13. (canceled)
14. The mote system of claim 1, wherein said directional antenna system operably coupled with said antenna signal detection unit further comprises:
an antenna steering unit.
15. The mote system of claim 14, wherein said antenna steering unit further comprises:
an electro-mechanical system.
16. The mote system of claim 14, wherein said antenna steering unit further comprises:
a micro-electro-mechanical system.
17. The mote system of claim 14, wherein said antenna steering unit further comprises:
an electromagnetic system.
18. The mote system of claim 1, further comprising:
a mote having said directional antenna system operably coupled with said antenna signal detection unit.
19. The mote system of claim 18, further comprising:
a fastener configured to hold at least one of an animate or inanimate unit in physical contact with said mote having said directional antenna system operably coupled with said antenna signal detection unit.
20. A mote method of using comprising:
distributing a mote, the mote having
(i) an antenna signal detection unit, and
(ii) a directional antenna system operably couplable with an antenna signal detection unit said directional antenna system including:
an antenna control unit configured to direct a movement of a field of regard of a directional antenna such that the field of regard of the directional antenna will likely operably align with a beam of an other directional antenna.
21. The mote method of claim 20, wherein said distributing a mote further comprises:
emplacing at least one unit in physical contact with the mote.
22. The mote method of claim 21, wherein said emplacing at least one unit in physical contact with the mote further comprises:
positioning an inanimate component in physical contact with the mote.
23. The mote method of claim 21, wherein said emplacing at least one unit in physical contact with the mote further comprises:
positioning an animate component in physical contact with the mote.
24. A mote method of making comprising:
forming a mote body; and
emplacing a directional antenna and an antenna control unit proximate to the mote body.
25. The mote method of claim 24, wherein said forming a mote body further comprises:
forming at least a part of the mote body from a substrate.
26. The mote method of claim 24, wherein said emplacing a directional antenna and an antenna control unit proximate to the mote body further comprises:
forming at least a part of the directional antenna from a substrate.
27. The mote method of claim 24, wherein said emplacing a directional antenna and an antenna control unit proximate to the mote body further comprises:
affixing at least a part of the directional antenna to the mote body.
28. A mote method comprising:
integrating a directional antenna and an antenna control unit proximate to a mote body with at least one unit.
29. The mote method of claim 28, wherein said integrating a directional antenna and an antenna control unit proximate to a mote body with at least one unit further comprises:
at least one of affixing the mote body to or encasing the mote body in an inanimate structural component.
30. The mote method of claim 28, wherein said integrating a directional antenna and an antenna control unit proximate to a mote body with at least one unit further comprises:
at least one of affixing the mote body to or encasing the mote body in an animate structural component.
31. The mote system of claim 1, wherein said antenna signal detection unit further comprises:
a correlation detector having a reference signal.
32. The mote system of claim 1, wherein said antenna signal detection unit further comprises:
an antenna control unit operably coupled to direct said antenna signal detection unit to vary a reference frequency of a demodulator.
33. The mote system of claim 1, wherein said antenna signal detection unit further comprises:
an antenna control unit operably coupled to direct said antenna signal detection unit to maintain a first reference frequency of a demodulator in association with a first rate of movement of a field of regard of the directional antenna and a second reference frequency of a demodulator in association with a second rate of movement of a field of regard of the directional antenna.
34. The mote system of claim 1, wherein said antenna signal detection unit further comprises:
an antenna control unit operably coupled to direct said antenna signal detection unit to determine one or more times during which a received signal strength of a beacon signal was at one or more substantially maximum values.
35. The mote system of claim 1, wherein said antenna signal detection unit further comprises:
an antenna control unit operably coupled to direct said antenna signal detection unit to determine one or more locations along an arc of movement of the directional antenna that correspond with one or more times at which a received signal strength of a beacon signal were at one or more substantially maximum values.
36. The mote system of claim 1, wherein said antenna control unit configured to direct a movement of a field of regard of a directional antenna such that the field of regard of the directional antenna will likely operably align with a beam of an other directional antenna further comprises:
an antenna control unit configured to direct a sweep of a field of regard of a directional antenna at a rate likely to be different from that of a rate of sweep of a beam of an other directional antenna.
37. The mote system of claim 1, wherein said antenna control unit configured to direct a movement of a field of regard of a directional antenna such that the field of regard of the directional antenna will likely operably align with a beam of an other directional antenna further comprises:
an antenna control unit configured to direct a rotation of a field of regard of a directional antenna at a rate of rotation varied by a quasi-random amount from a nominal rate of rotation.
38. The mote system of claim 1, wherein said antenna control unit configured to direct a movement of a field of regard of a directional antenna such that the field of regard of the directional antenna will likely operably align with a beam of an other directional antenna further comprises:
an antenna control unit configured to direct a movement of a field of regard of a directional antenna at a quasi-randomly selected rate of movement.
39. The mote system of claim 1, wherein said antenna control unit configured to direct a movement of a field of regard of a directional antenna such that the field of regard of the directional antenna will likely operably align with a beam of an other directional antenna further comprises:
an antenna control unit configured to direct a movement of a field of regard of a directional antenna at a quasi-randomly selected period of time.
40. The mote system of claim 1, wherein said antenna control unit configured to direct a movement of a field of regard of a directional antenna such that the field of regard of the directional antenna will likely operably align with a beam of an other directional antenna further comprises:
an antenna control unit configured to direct a rate of rotation of a field of regard of a directional antenna at a rate likely to be different from that of a rate of rotation of a beam of an other directional antenna.
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 nozzle segment, wherein a plurality of said turbine nozzle segments provide for forming an associated turbine nozzle when circumferentially disposed in cooperative relationship with one another about a central axis, said turbine nozzle segment comprising:
a. an inner endwall portion;
b. an outer endwall portion, wherein said inner and outer endwall portions are each generally curved about said central axis, and said outer endwall portion is generally outside said inner endwall portion relative to said central axis;
c. a first portion of a first bounding nozzle vane, wherein said first portion of said first bounding nozzle vane extends between said inner and outer endwall portions at a first azimuthal boundary of said turbine nozzle segment;
d. a second portion of a second bounding nozzle vane, wherein said second portion of said second bounding nozzle vane extends between said inner and outer endwall portions at a second azimuthal boundary of said turbine nozzle segment, and said first and second azimuthal boundaries are azimuthally displaced from one another relative to said central axis;
e. at least one annular-segment passage, wherein said at least one annular-segment passage is bounded by said inner and outer endwall portions, one said at least one annular-segment passage is bounded by said first portion of said first bounding nozzle vane and one said at least one annular-segment passage is bounded by said second portion of said second bounding nozzle vane, a first external boundary of said first portion of said first bounding nozzle vane is shaped so as to provide for mating with a second external boundary of said second portion of said second bounding nozzle vane when said first portion of said first bounding nozzle vane is part of said turbine nozzle segment and said second portion of said second bounding nozzle vane is part of a first other turbine nozzle segment, or when said second portion of said second bounding nozzle vane is part of said turbine nozzle segment and said first portion of said first bounding nozzle vane is part of a second other turbine nozzle segment, and said first portion of said first bounding nozzle vane, said second portion of said second bounding nozzle vane and said first and second external boundaries are shaped so that said second portion of said second bounding nozzle vane of said first other turbine nozzle segment and said first portion of said first bounding nozzle vane of said turbine nozzle segment when azimuthally abutted against one another constitute said first bounding nozzle vane, and said first portion of said first bounding nozzle vane of said second other turbine nozzle segment and said second portion of said second bounding nozzle vane of said turbine nozzle segment when azimuthally abutted against one another constitute said second bounding nozzle vane, wherein each said first and second other turbine nozzle segment is shaped substantially the same as said turbine nozzle segment.
2. A turbine nozzle segment as recited in claim 1, wherein said first portion of said first bounding nozzle vane is continuous with at least respective first portions of both said inner and outer endwall portions, respectively, and said second portion of said second bounding nozzle vane is continuous with at least respective second portions of both said inner and outer endwall portions, respectively.
3. A turbine nozzle segment as recited in claim 2, further comprising:
a. a first fillet between said first portion of said first bounding nozzle vane and said first portion of said inner endwall portion;
b. a second fillet between said first portion of said first bounding nozzle vane and said first portion of said outer endwall portion;
c. a third fillet between said second portion of said second bounding nozzle vane and said second portion of said inner endwall portion; and
d. a fourth fillet between said second portion of said second bounding nozzle vane and said second portion of said outer endwall portion.
4. A turbine nozzle segment as recited in claim 2, wherein said first and second portions of said inner endwall portion are continuous with one another, and said first and second portions of said outer endwall portion are continuous with one another.
5. A turbine nozzle segment as recited in claim 2, wherein said first and second portions of said inner endwall portion are distinct from one another and joined to one another at a boundary therebetween, and said first and second portions of said outer endwall portion are distinct from one another and joined to one another at a boundary therebetween.
6. A turbine nozzle segment as recited in claim 5, wherein said first and second portions of said inner endwall portion are joined to one another at said boundary therebetween by welding or brazing, and said first and second portions of said outer endwall portion are joined to one another at said boundary therebetween by welding or brazing.
7. A turbine nozzle segment as recited in claim 1, wherein said first portion of said first bounding nozzle vane comprises a suction side of said first bounding nozzle vane, and said second portion of said second bounding nozzle vane comprises a pressure side of said second bounding nozzle vane.
8. A turbine nozzle segment as recited in claim 1, wherein said first portion of said first bounding nozzle vane extends from a leading edge to a trailing edge of said first bounding nozzle vane, and said second portion of said second bounding nozzle vane extends from a leading edge to a trailing edge of said second bounding nozzle vane.
9. A turbine nozzle segment as recited in claim 8, wherein said leading edge of said first portion of said first bounding nozzle vane comprises a first sealing surface, said leading edge of said second portion of said second bounding nozzle vane comprises a second sealing surface, said trailing edge of said first portion of said first bounding nozzle vane comprises a third sealing surface, said trailing edge of said second portion of said second bounding nozzle vane comprises a fourth sealing surface, and said first and second sealing surfaces are adapted to cooperate with one another so as to provide for sealing a first junction therebetween for different said turbine nozzle segments, and said third and fourth sealing surfaces are adapted to cooperate with one another so as to provide for sealing a second junction therebetween for different said turbine nozzle segments, so as to provide for sealing an interior of a corresponding first or second bounding vane defined thereby.
10. A turbine nozzle segment as recited in claim 9, further comprising a first feather seal that provides for the cooperation between said first and second sealing surfaces; and a second feather seal that provides for the cooperation between said third and fourth sealing surfaces.
11. A turbine nozzle segment as recited in claim 1, wherein said at least one annular-segment passage comprises a single annular-segment passage bounded in part by said first portion of said first bounding nozzle vane and by said second portion of said second bounding nozzle vane.
12. A turbine nozzle segment as recited in claim 1, wherein said at least one annular-segment passage comprises a plurality of annular-segment passages and at least one complete nozzle vane azimuthally therebetween.
13. A turbine nozzle segment as recited in claim 1, wherein said at least one annular-segment passage comprises an inlet and an outlet, and an effective through-flow area of said at least one annular-segment passage at said outlet does not exceed a corresponding effective through-flow area elsewhere within said at least one annular-segment passage.
14. A turbine nozzle segment as recited in claim 1, further comprising at least one of:
a. a first impingement liner portion operatively coupled to an exterior portion of said first portion of said first bounding nozzle vane relative to said turbine nozzle segment, wherein said first impingement liner portion incorporates a plurality of impingement cooling holes in fluid communication with at least one first cavity between said first impingement liner portion and said first portion of said first bounding nozzle vane, and said first portion of said first bounding nozzle vane incorporates a plurality of cooling holes that provide for fluid communication between said at least one first cavity and said at least one annular-segment passage, and
b. a second impingement liner portion operatively coupled to an exterior portion of said second portion of said second bounding nozzle vane relative to said turbine nozzle segment, wherein said second impingement liner portion incorporates a plurality of impingement cooling holes in fluid communication with at least one second cavity between said second impingement liner portion and said second portion of said second bounding nozzle vane, and said second portion of said second bounding nozzle vane incorporates a plurality of cooling holes that provide for fluid communication between said at least one second cavity and said at least one annular-segment passage.
15. A turbine nozzle segment as recited in claim 14, wherein the operative coupling of said first impingement liner portion if present to said first portion of said first bounding nozzle vane comprises welding or sealing said first impingement liner portion along a substantial portion of a first periphery thereof and the operative coupling of said second impingement liner portion if present to said second portion of said second bounding nozzle vane comprises welding or sealing said second impingement liner portion along a substantial portion of a second periphery thereof.
16. A turbine nozzle segment as recited in claim 1, wherein said turbine nozzle segment is manufactured by either hydroforming or explosively forming a tubular material within a plurality of dies.
17. A turbine nozzle segment as recited in claim 1, wherein said turbine nozzle segment is manufactured by either casting or sintering.
18. A turbine nozzle segment as recited in claim 5, wherein said turbine nozzle segment is manufactured by stamping said first portion of said first bounding nozzle vane together with said first portions of said inner and outer endwall portions, and separately stamping said second portion of said second bounding nozzle vane together with said second portions of said inner and outer endwall portions.
19. A turbine nozzle segment as recited in claim 1, wherein said turbine nozzle segment is replicated so as to provide for said plurality of said turbine nozzle segments, said plurality of said turbine nozzle segments are assembled azimuthally abutting one another about said central axis so as to form said turbine nozzle, and for each said turbine nozzle segment in said turbine nozzle, said first portion of said first bounding nozzle vane of said turbine nozzle segment abuts said second portion of said second bounding nozzle vane of said first other turbine nozzle segment, and said second portion of said second bounding nozzle vane of said turbine nozzle segment abuts said first portion of said first bounding nozzle vane of said second other turbine nozzle segment.
20. A turbine nozzle segment as recited in claim 19, wherein at least one said turbine nozzle segment is welded or brazed to said first other turbine nozzle segment at a first joint where said first portion of said first bounding nozzle vane of said turbine nozzle segment abuts said second portion of said second bounding nozzle vane of said first other turbine nozzle segment, or at least one said turbine nozzle segment is welded or brazed to said second other turbine nozzle segment at a second joint where said second portion of said second bounding nozzle vane of said turbine nozzle segment abuts said first portion of said first bounding nozzle vane of said second other turbine nozzle segment.
21. A turbine nozzle segment as recited in claim 19, further comprising at least one impingement liner inserted within an interior of a corresponding at least one said first or second bounding nozzle vane.
22. A turbine nozzle segment as recited in claim 21, wherein said at least one impingement liner is substantially sealed along a radially-outer periphery to at least one of:
a. a corresponding said outer endwall portion of at least one of said turbine nozzle segment and one of said first or second other turbine nozzle segment, and
b. a radially-outer portion of an interior surface of said first or second bounding nozzle vane, and
said at least one impingement liner is substantially sealed along a radially-inner periphery to at least one of:
c. a corresponding said inner endwall portion of at least one of said turbine nozzle segment and one of said first or second other turbine nozzle segment, and
d. a radially-inner portion of an interior surface of said first or second bounding nozzle vane.
23. A turbine nozzle segment as recited in claim 22, wherein said at least one impingement liner is substantially sealed with either a welded or brazed joint.
24. A method of manufacturing a turbine nozzle, comprising: assembling a plurality of turbine nozzle segments to one another so as to form a turbine nozzle incorporating a plurality of nozzle vanes, wherein each turbine nozzle segment of said plurality of turbine nozzle segments comprises:
a. inner and outer circumferential endwall portions;
b. a first portion of a first bounding nozzle vane bounded at a first azimuthal boundary extending through and bisecting said first bounding nozzle vane; and
c. a second portion of a second bounding nozzle vane bounded at a second azimuthal boundary extending through and bisecting said second bounding nozzle vane; and
the operation of assembling said plurality of turbine nozzle segments to one another comprises operatively coupling said first portion of said first bounding nozzle vane of a first turbine nozzle segment of said plurality of turbine nozzle segments to said second portion of said second bounding nozzle vane of a second turbine nozzle segment of said plurality of turbine nozzle segments so as to form a corresponding nozzle vane of said plurality of nozzle vanes, for at least one first turbine nozzle segment and at least one second turbine nozzle segment of said plurality of turbine nozzle segments of said turbine nozzle.
25. A method of manufacturing a turbine nozzle as recited in claim 24, further comprising forming at least one turbine nozzle segment of said plurality of turbine nozzle segments.
26. A method of manufacturing a turbine nozzle as recited in claim 25, wherein in the operation of forming said at least one turbine nozzle segment of said plurality of turbine nozzle segments, said at least one said turbine nozzle segment of said plurality of turbine nozzle segments is formed by either hydroforming or explosively forming a tubular material within a plurality of dies.
27. A method of manufacturing a turbine nozzle as recited in claim 25, wherein in the operation of forming said at least one turbine nozzle segment of said plurality of turbine nozzle segments, said at least one said turbine nozzle segment of said plurality of turbine nozzle segments is formed by either casting or sintering.
28. A method of manufacturing a turbine nozzle as recited in claim 25, wherein in the operation of forming said at least one turbine nozzle segment of said plurality of turbine nozzle segments, said at least one said turbine nozzle segment of said plurality of turbine nozzle segments is formed by stamping said first portion of said first bounding nozzle vane together with first portions of said inner and outer circumferential endwall portions, and separately stamping said second portion of said second bounding nozzle vane together with second portions of said inner and outer circumferential endwall portions.
29. A method of manufacturing a turbine nozzle as recited in claim 24, further comprising drilling a plurality of cooling holes through at least one of a portion of said first bounding nozzle vane of at least one said turbine nozzle segment, and a portion of said second bounding nozzle vane of at least one said turbine nozzle segment, wherein the operation of drilling said plurality of cooling holes is performed prior to the operation of assembling said plurality of turbine nozzle segments to one another so as to form said turbine nozzle and said plurality of nozzle vanes.
30. A method of manufacturing a turbine nozzle as recited in claim 24, further comprising at least one of:
a. operatively coupling a first impingement liner portion to a first internal surface of said first bounding nozzle vane of at least one said turbine nozzle segment, wherein said first impingement liner portion incorporates a first plurality of impingement cooling holes therethrough, said first plurality of impingement cooling holes are offset from said first internal surface of said first bounding nozzle vane, said first internal surface of said first bounding nozzle vane is external of said turbine nozzle segment prior to assembly thereof into said turbine nozzle, and the operation of operatively coupling said first impingement liner portion to said first internal surface of said first bounding nozzle vane of said at least one said turbine nozzle segment is performed prior to the operation of assembling said plurality of turbine nozzle segments to one another so as to form said turbine nozzle and said plurality of nozzle vanes; and
b. operatively coupling a second impingement liner portion to a second internal surface of said second bounding nozzle vane of at least one said turbine nozzle segment, wherein said second impingement liner portion incorporates a second plurality of impingement cooling holes therethrough, said second plurality of impingement cooling holes are offset from said second internal surface of said second bounding nozzle vane, said second internal surface of said second bounding nozzle vane is external of said turbine nozzle segment prior to assembly thereof into said turbine nozzle, and the operation of operatively coupling said second impingement liner portion to said second internal surface of said second bounding nozzle vane of said at least one said turbine nozzle segment is performed prior to the operation of assembling said plurality of turbine nozzle segments to one another so as to form said turbine nozzle and said plurality of nozzle vanes.
31. A method of manufacturing a turbine nozzle as recited in claim 30, wherein the operation of operatively coupling said first impingement liner portion to said first internal surface of said first bounding nozzle vane of said at least one said turbine nozzle segment comprises sealing said first impingement liner portion to said first internal surface along a substantial portion of a first closed path along said first impingement liner portion either on or within a periphery thereof, and the operation of operatively coupling said second impingement liner portion to said second internal surface of said second bounding nozzle vane of said at least one said turbine nozzle segment comprises sealing said second impingement liner portion to said second internal surface along a substantial portion of a second closed path along said second impingement liner portion either on or within a periphery thereof.
32. A method of manufacturing a turbine nozzle as recited in claim 31, wherein at least one of the operations of sealing said first and second impingement liner portions respectively to said first and second internal surfaces comprise either welding or brazing.
33. A method of manufacturing a turbine nozzle as recited in claim 24, wherein the operation of assembling said plurality of turbine nozzle segments comprises: for each said turbine nozzle segment of said plurality of turbine nozzle segments incorporated in said turbine nozzle, azimuthally abutting said first azimuthal boundary of said first bounding nozzle vane of said turbine nozzle segment to said second azimuthal boundary of said second bounding nozzle vane of a first other said turbine nozzle segment of said plurality of turbine nozzle segments so as to form one of said plurality of nozzle vanes of said turbine nozzle, and azimuthally abutting said second azimuthal boundary of said second bounding nozzle vane of said turbine nozzle segment to said first azimuthal boundary of said first bounding nozzle vane of a second other said turbine nozzle segment of said plurality of turbine nozzle segments so as to form another of said plurality of nozzle vanes of said turbine nozzle.
34. A method of manufacturing a turbine nozzle as recited in claim 24, wherein the operation of assembling said plurality of turbine nozzle segments comprises assembling said plurality of turbine nozzle segments over a cylindrical mandrel.
35. A method of manufacturing a turbine nozzle as recited in claim 24, wherein for at least one said turbine nozzle segment of said plurality of turbine nozzle segments, the operation of assembling said plurality of turbine nozzle segments comprises at least one of:
a. welding or brazing said first azimuthal boundary of said turbine nozzle segment to said second azimuthal boundary of a first other turbine nozzle segment so as to form one of said plurality of nozzle vanes of said turbine nozzle, and
b. welding or brazing said second azimuthal boundary of said turbine nozzle segment to said first azimuthal boundary of a second other turbine nozzle segment so as to form another of said plurality of nozzle vanes of said turbine nozzle.
36. A method of manufacturing a turbine nozzle as recited in claim 24, wherein for at least one said turbine nozzle segment of said plurality of turbine nozzle segments, the operation of assembling said plurality of turbine nozzle segments comprises at least one of:
a. sealing said first azimuthal boundary of said turbine nozzle segment to said second azimuthal boundary of a first other turbine nozzle segment so as to form one of said plurality of nozzle vanes of said turbine nozzle, and
b. sealing said second azimuthal boundary of said turbine nozzle segment to said first azimuthal boundary of a second other turbine nozzle segment so as to form another of said plurality of nozzle vanes of said turbine nozzle.
37. A method of manufacturing a turbine nozzle as recited in claim 24, further comprising configuring each of said plurality of turbine nozzle segments so that an outlet thereof is located at and defines a throat of said turbine nozzle.
38. A method of manufacturing a turbine nozzle as recited in claim 24, further comprising inserting at least one impingement liner within an interior of a corresponding at least one said nozzle vane, wherein said at least one impingement liner comprises a plurality of impingement cooling holes through a surface thereof.
39. A method of manufacturing a turbine nozzle as recited in claim 38, further comprising sealing at least substantial portions of radially-outer and radially-inner peripheries of said at least one impingement liner to corresponding portions of said corresponding at least one said nozzle vane.
40. A method of manufacturing a turbine nozzle as recited in claim 38, wherein said at least one impingement liner is inserted within said interior of said corresponding at least one said nozzle vane following the operation of operatively coupling said first portion of said first bounding nozzle vane of said first turbine nozzle segment of said plurality of turbine nozzle segments to said second portion of said second bounding nozzle vane of said second turbine nozzle segment of said plurality of turbine nozzle segments.
41. A method of manufacturing a turbine nozzle as recited in claim 38, wherein said at least one impingement liner is inserted within said interior of said corresponding at least one said nozzle vane adjacent to one of said first portion of said first bounding nozzle vane of said first turbine nozzle segment of said plurality of turbine nozzle segments and said second portion of said second bounding nozzle vane of said second turbine nozzle segment of said plurality of turbine nozzle segments prior to the operation of operatively coupling said first portion of said first bounding nozzle vane of said first turbine nozzle segment of said plurality of turbine nozzle segments to said second portion of said second bounding nozzle vane of said second turbine nozzle segment of said plurality of turbine nozzle segments.