A preswirler of a gas turbine engine includes an outer ring. The outer ring includes an outer flange with a plurality of first holes, and an outer cylindrical portion extending from the outer flange. The preswirler also includes an inner ring. The inner ring includes an inner flange spaced apart fro
A preswirler of a gas turbine engine includes an outer ring. The outer ring includes an outer flange with a plurality of first holes, and an outer cylindrical portion extending from the outer flange. The preswirler also includes an inner ring. The inner ring includes an inner flange spaced apart from the outer flange. The inner ring also includes an inner cylindrical portion located within the outer cylindrical portion and a back portion extending from the inner flange to the inner cylindrical portion. The inner ring further includes a plurality of second holes.
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1. A gas turbine engine, comprising: a diaphragm having a mounting portion including a first surface,a second surface opposite the first surface,a plurality of outer diameter holes,a plurality of inner diameter holes,a plurality of cooling holesa plurality of blind holes adjacent to the plurality of
1. A gas turbine engine, comprising: a diaphragm having a mounting portion including a first surface,a second surface opposite the first surface,a plurality of outer diameter holes,a plurality of inner diameter holes,a plurality of cooling holesa plurality of blind holes adjacent to the plurality of inner diameter holes anda plurality of lock plates located between the plurality of inner diameter couplers and the first surface;a preswirler having an outer ring including an outer flange including a first forward surface in contact with the second surface,an outer cylindrical portion extending from the outer flange, anda plurality of first holes in the outer flange, andan inner ring including an inner flange spaced apart from the outer flange defining an opening for cooling air in flow communication with the plurality of cooling holes therebetween, the inner flange including a second forward surface in contact with the second surface,an inner cylindrical portion located within the outer cylindrical portion defining an annular chamber for cooling air therebetween, anda back portion extending from the inner flange to the inner cylindrical portion, anda plurality of second holes in the inner ring;wherein the outer flange, the inner flange, and the back portion define a radial chamber for cooling air therebetween, the radial chamber being in flow communication with the annular chamber and the opening;a plurality of outer diameter couplers, wherein the plurality of outer diameter holes are aligned with the plurality of first holes, and where each of the plurality of outer diameter couplers passes through an outer diameter hole and into a first hole; anda plurality of inner diameter couplers, wherein the plurality of inner diameter holes are aligned with the plurality of second holes, and where each of the plurality of inner diameter couplers passes through an inner diameter hole and into a second hole. 2. The gas turbine engine of claim 1, wherein the plurality of second holes are in the inner flange. 3. The gas turbine engine of claim 1, wherein the inner ring includes a plurality of bosses with a second hole in each boss. 4. The gas turbine engine of claim 3, wherein each boss is welded to the inner ring. 5. The gas turbine engine of claim 1, wherein the plurality of first holes total more than ten, the plurality of second holes total more than ten, the plurality of outer diameter holes total more than ten, and the plurality of inner diameter holes total more than ten. 6. The gas turbine engine of claim 1, further comprising a plurality of spacers located between the plurality of outer diameter couplers and the first surface. 7. The gas turbine engine of claim 1, wherein the plurality of first holes and the plurality of second holes are threaded, and the plurality outer diameter couplers and the plurality of inner diameter couplers are bolts. 8. A method for mounting a preswirler of a gas turbine engine to a diaphragm, the diaphragm having a mounting portion including a first surface, a second surface, a cavity to retain the preswirler with a press fit, and a plurality of outer diameter holes, and the preswirler having an outer ring including an outer flange with a plurality of first holes in the outer flange, and an inner ring including an inner flange spaced apart from the outer flange and a back portion extending from the inner flange, the method comprising: machining a plurality of through holes through the inner ring;inserting one of a plurality of bosses into each of the plurality of through holes;welding the plurality of bosses to the inner ring;machining a second hole into each of the plurality of bosses;machining a plurality of inner diameter holes through the mounting portion from the first surface to the second surface;decreasing the press fit between the preswirler and the diaphragm; andcoupling the preswirler to the diaphragm by inserting an outer diameter coupler through each outer diameter hole and into a first hole, andinserting an inner diameter coupler through each inner diameter hole and into a second hole. 9. The method of claim 8, wherein a blind hole is machined into the mounting portion through the first surface adjacent to each inner diameter hole. 10. The method of claim 8, wherein the plurality of through holes total more than ten and the plurality of bosses total more than ten. 11. The method of claim 8, wherein threaded holes are machined into each of the plurality of bosses. 12. A method for mounting a preswirler of a gas turbine engine to a diaphragm, the diaphragm having a mounting portion including a first surface, a second surface, and a plurality of outer diameter holes, and the preswirler having an outer ring including an outer flange with a plurality of first holes in the outer flange, and an inner ring including an inner flange spaced apart from the outer flange and a back portion extending from the inner flange, the method comprising: machining a plurality of through holes through the inner ring;inserting one of a plurality of bosses into each of the plurality of through holes;welding the plurality of bosses to the inner ring;machining a second hole into each of the plurality of bosses;machining a plurality of inner diameter holes through the mounting portion from the first surface to the second surface machining a blind hole into the mounting portion through the first surface adjacent to each inner diameter hole; andcoupling the preswirler to the diaphragm by inserting an outer diameter coupler through each outer diameter hole and into a first hole, andinserting an inner diameter coupler through each inner diameter hole and into a second hole. 13. The method of claim 8, wherein the mounting portion having a cavity to retain the preswirler with a press fit, further comprising: decreasing the press fit between the preswirler and the diaphragm. 14. The method of claim 8, wherein the plurality of through holes total more than ten and the plurality of bosses total more than ten. 15. The method of claim 8, wherein threaded holes are machined into each of the plurality of bosses.
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이 특허에 인용된 특허 (8)
Neal Peter F. (Derby GB2), Air cooling systems for gas turbine engines.
Mize Christopher D. (Palm Beach Gardens FL) Pirsig William W. (Manchester CT) Vercellone Peter T. (North Haven CT), Anti-contamination thrust balancing system for gas turbine engines.
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