Patents Represented by Attorney Edward L. Kochey, Jr.

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  • Manufacturer of brush seals
    Patent number: 5732466
    Abstract: Excess length 20 of brush seal wires 14 is sheared off with a punch 30 and die 26. A true and accurate diameter 22 is formed. The wires can be ground to a final finish diameter 18 if desired.
    Type: Grant
    Filed: November 21, 1994
    Date of Patent: March 31, 1998
    Assignee: United Technologies Corporation
    Inventor: Joseph Paul Bouchard
  • Bulkhead liner with raised lip
    Patent number: 5581999
    Abstract: Bulkhead 14 is conical and therefore the surface of bulkhead liners 30 has a curved or arcuate surface 68. Raised lip 70 with planar surface 72 is adjacent and surrounded in each opening 20. Fuel nozzle guide 24 may be rotated against and sealed to the surface of the liner segments.
    Type: Grant
    Filed: December 15, 1994
    Date of Patent: December 10, 1996
    Assignee: United Technologies Corporation
    Inventor: Thomas E. Johnson
  • Gas turbine engine spline arrangement
    Patent number: 5580183
    Abstract: A hollow drive shalt (20) with external splines (26) and drives a hollow driven shalt (14) which has internal splines (32). The driven shalt (14) thickness is uniformly tapered in the spline area, while the drive shalt (20) has a constant thickness through part of the spline area, and then a uniformly reducing thickness toward the unloaded end. The teeth of the external spline are crowned with the peak toward the loaded end of the drive spline (26). A flat is located at this peak.
    Type: Grant
    Filed: April 29, 1994
    Date of Patent: December 3, 1996
    Assignee: United Technologies Corporation
    Inventors: Russell F. Brackoneski, Dennis F. Buono, John P. Abrahamian
  • Fuel nozzle guide retainer assembly
    Patent number: 5577379
    Abstract: Fuel nozzle guide 24 is threaded to fuel nozzle guide retainer 26, entrapping bulkhead 14, bulkhead liner 30 and key washer 28. Internal tabs 74 lock within slot 76 in the threads of the fuel nozzle guide. External tabs 78 of the key washer are bent into slot 80 of the retainer 26, after the nozzle guide 24 and the retainer are threaded together.
    Type: Grant
    Filed: December 15, 1994
    Date of Patent: November 26, 1996
    Assignee: United Technologies Corporation
    Inventor: Thomas E. Johnson
  • Bulkhead cooling fairing
    Patent number: 5542246
    Abstract: Cooling air flow from behind bulkhead liner segments 30 and from behind float wall panels 42 is guided as flow 50 over the hot surface of the bulkhead liner segments by fairing 44. The fairing is secured between a shell (38,40) and a float wall panel 42, and being of equal and coincident length as the panel, may be replaced with the removal of only one panel.
    Type: Grant
    Filed: December 15, 1994
    Date of Patent: August 6, 1996
    Assignee: United Technologies Corporation
    Inventors: Thomas E. Johnson, Craig G. Thompson
  • Gas turbine engine feather seal arrangement
    Patent number: 5531457
    Abstract: Adjacent platforms (16) have feather seals (34) in complementary slots (22). Hot grooves (40) carry cooling air across the seal and discharge it into the gap (20) between adjacent platforms. Grooves discharging from abutting surfaces are staggered and have a flow component parallel to the axial gas flow through the turbine.
    Type: Grant
    Filed: December 7, 1994
    Date of Patent: July 2, 1996
    Assignee: Pratt & Whitney Canada, Inc.
    Inventors: Ian Tibbott, Roger Gates
  • Segmented bulkhead liner for a gas turbine combustor
    Patent number: 5524438
    Abstract: Truncated pie shaped bulkhead liner sections 60 are each divided into two liner segments 62. The division occurs adjacent fuel nozzle opening 20. Upstream extending lips 71, 75 and 77 abut the bulkhead 14. Cooling air passes through cooling flow openings in the bulkhead with all the flow continuing toward the shell 38, 40 edges of the liner segments.
    Type: Grant
    Filed: December 15, 1994
    Date of Patent: June 11, 1996
    Assignee: United Technologies Corporation
    Inventors: Thomas E. Johnson, Thomas J. Madden, Robert W. Soderquist
  • Aircraft fan containment structure restraint
    Patent number: 5516257
    Abstract: Woven fiber ballistic fabric (22) of multiple layers surrounds an isogrid support structure (20). A cuff portion (38) has shorter warp threads than the major portion (3) and also is impregnated with epoxy resin. A diameter restrains the fabric from aft movement during a blade ejection event.
    Type: Grant
    Filed: April 28, 1994
    Date of Patent: May 14, 1996
    Assignee: United Technologies Corporation
    Inventors: Robert F. Kasprow, Kurt M. Dembeck, Grant Eckfeldt
  • Axisymmetric vectoring nozzle
    Patent number: 5511376
    Abstract: A convergent/divergent nozzle (14) has five trains of flaps. Each train is comprised of an inboard (26) and outboard (20) convergent flap, an inboard (48) and outboard (44) divergent flap and an external flap (62). The five external flaps (62) maintain their symmetry while vectoring, whereby overlapping of adjacent flaps is obtained. The inboard and outboard convergent flaps are individually driven (32,36) by a common unison ring (28).
    Type: Grant
    Filed: November 1, 1994
    Date of Patent: April 30, 1996
    Assignee: United Technologies Corporation
    Inventor: William K. Barcza
  • Variable thickness isogrid case
    Patent number: 5485723
    Abstract: A light weight isogrid containment structure has minor concessions to weight in order to achieve efficient manufacture oversize flanges are permitted in skin thickness interface zones so that manufacture may be accomplished with fewer milling tools and tool changes.
    Type: Grant
    Filed: April 29, 1994
    Date of Patent: January 23, 1996
    Assignee: United Technologies Corporation
    Inventors: Jeffrey P. McCoy, Allan R. Penda
  • Gas turbine airfoil clocking
    Patent number: 5486091
    Abstract: The first stage of vanes (16) and second stage of vanes (24) each contain the same number of vanes. The second stage vanes are located such that the wake flow (38) from the first stage vanes falls on or near the leading edge, after passing through the stage of rotating blades.
    Type: Grant
    Filed: April 19, 1994
    Date of Patent: January 23, 1996
    Assignee: United Technologies Corporation
    Inventor: Om P. Sharma
  • Gas turbine engine combustion liner float wall cooling arrangement
    Patent number: 5461866
    Abstract: When second shell section 18 diverges with respect to first shell section 16, the second liner panel 50 is located with a changing spacing from the shell. The liner is close to the shell at the upstream edge 68, and farther from the liner at the downstream end 57. The downstream end of the first liner panel 64 overlaps the second liner panel 50 on the gas side.
    Type: Grant
    Filed: December 15, 1994
    Date of Patent: October 31, 1995
    Assignee: United Technologies Corporation
    Inventors: Dennis J. Sullivan, Aaron S. Butler, Mark A. Kelley
  • Compressor stator vane assembly
    Patent number: 5462403
    Abstract: The arcuate vane support segments (26) each carry a plurality of vanes (28) and have a pair of axially extending feet (38). These feet do not slide axially into a groove, but move radially against an arm (22) of the "T" shaped air seal. The casing ring 62 is translated axially in place entrapping the feet (38).
    Type: Grant
    Filed: March 21, 1994
    Date of Patent: October 31, 1995
    Assignee: United Technologies Corporation
    Inventor: John L. Pannone
  • Turbine blade damper and seal
    Patent number: 5460489
    Abstract: A flexible seal (26) is located beneath blade platform (14) with end seals (28) in contact with adjacent platforms. A friction damper (34) formed of a flat slug of metal is supported only by the flexible seal (26) and in particular by the center section (32) of the seal.
    Type: Grant
    Filed: April 12, 1994
    Date of Patent: October 24, 1995
    Assignee: United Technologies Corporation
    Inventors: Robert B. Benjamin, Betsy B. Adams
  • Hollow titanium blade manufacturing
    Patent number: 5448829
    Abstract: A titanium gas injection tube 18 is located within a counterbore (16) in the blade (10) halves which are to be bonded and formed. An internal stainless steel sleeve (24) is placed in the counterbore inside the titanium tube to resist bonding forces. An external stainless steel sleeve (28) is placed around the tube to resist gas pressure forces.
    Type: Grant
    Filed: January 31, 1994
    Date of Patent: September 12, 1995
    Assignee: United Technologies Corporation
    Inventors: James R. Dillner, Peter E. Leibfried
  • Cooled gas turbine blade
    Patent number: 5431537
    Abstract: A hollow air cooled airfoil blade (10) castable with a single pull core and having internal trip strips (28) at the leading edge. Parallel ribs (16,18) extend from the pressure side (12) of the blade to the suction side (14). A parting line (32) passes through the most forward point (34) of the airfoil, this being located on the suction side of the leading edge (36). The trip strips stop short of the parting line.
    Type: Grant
    Filed: April 19, 1994
    Date of Patent: July 11, 1995
    Assignee: United Technologies Corporation
    Inventor: Shimon Sturm
  • Sliding throat gas turbine engine nozzle
    Patent number: 5431344
    Abstract: Exit area control panels 18 are supported for movement at an angle with respect to the nozzle axis 12. A varying exit area is formed as actuator 26 axially positions the panels 18. In each exit area control panel 18, there is slidably supported a throat area control panel 28, driven by actuator 32. A sliding throat is achieved as the two panels 18,28 are moved in each quadrant. Yaw and pitch vectoring is accomplished with selective positioning of the two panels.
    Type: Grant
    Filed: November 12, 1993
    Date of Patent: July 11, 1995
    Assignee: United Technologies Corporation
    Inventors: Rudolph J. Novotny, David E. Wendt, Gary D. Jones, James S. Johnson
  • Hollow fan blade fabrication
    Patent number: 5419040
    Abstract: Purge flow openings through chordwise ribs in hollow fan blades are formed by making partial circular cuts at the rib edges before diffusion bonding the blade halves. A full semi-circular section is used on the pressure side, but only a segment of a semicircular section is used on the suction side.
    Type: Grant
    Filed: April 29, 1994
    Date of Patent: May 30, 1995
    Assignee: United Technologies Corporation
    Inventors: Michael A. Weisse, David B. Carter
  • Aircraft fan containment structure
    Patent number: 5413456
    Abstract: Isogrid structure (20) forms case (14) surrounding the fan blades. In the zones where blade penetration is anticipated, the ribs (38) of the lattice do not run circumferentially. The skin segments (48) are of different thickness in different zones, but do not differ more than 30% from the thickness of an adjoining segment.
    Type: Grant
    Filed: April 29, 1994
    Date of Patent: May 9, 1995
    Assignee: United Technologies Corporation
    Inventors: Andrew C. Kulak, Kurt M. Dembeck, Richard T. White
  • Gas turbine engine component retention
    Patent number: 5411369
    Abstract: A split retaining ring 22 has deep internal scallops 26 which clear lugs 36 during installation while the ring fits within lip 40. The ring is opened with ridges 30 clearing lugs 36 while the ring is rotated. Shallow internal scallops rest on and lock with lugs 36 in the final position.
    Type: Grant
    Filed: February 22, 1994
    Date of Patent: May 2, 1995
    Assignee: Pratt & Whitney Canada, Inc.
    Inventor: Jean G. Bouchard