公开(公告)号：JPH11264059A

公开(公告)日：1999-09-28

申请号：JP32621398

申请日：1998-11-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MALONEY MICHAEL J

IPC: F01D5/28 ,  B21D39/00 ,  B32B3/26 ,  B32B18/00 ,  C04B38/00 ,  C23C4/04 ,  C23C14/06 ,  C23C14/08 ,  C23C16/00 ,  C23C28/00 ,  C23D5/04 ,  F02C7/00

Abstract: PROBLEM TO BE SOLVED: To reduce thermal conductivity and improve wear resistance by making at least one layer of a layer like ceramic coating applied on a base body of high density and making at least one of other layer low density. SOLUTION: At least one layer of a porous ceramic layer coated on a base body is a porous layer having at least a volume porosity rate of about 20%, and one of other layer is substantially a non porosity layer having a volume porosity rate of about 5%. The ceramic material on a base body is obtained so that plural ceramic layers are vapor deposited and heat treated under conditions consequentially that at least one layer has a micro structure of a band region I and at least one of other layer has a micro structure selected from band regions II, III and a group of these combinations. A porous layer preferably includes a layer made of celia for a base material and a layer made of zirconia for a base material.

公开(公告)号：JPH11257101A

公开(公告)日：1999-09-21

申请号：JP37635998

申请日：1998-12-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： ANDERSON GILBERT L JR ,  BROWN DAMON K ,  HINTON BRUCE S ,  KELLY JAMES B

IPC: F02C9/00 ,  F02C9/28 ,  F02C9/44 ,  F04D27/00

Abstract: PROBLEM TO BE SOLVED: To improve the reliability of stall detection by detecting the stall of a gas turbine in engine on the basis of the intensity of ultraviolet rays to be detected by an augmenter when a burner pressure sensor fails and/or bursts out. SOLUTION: A gas turbine power unit 10 of aircraft, in an engine control 70, monitors a plurality of engine parameters, calculating the control data, and the variable geometry of a fuel flow and an engine is adjusted, thereby realizing the optimum engine operation. It is equipped with a burner pressure sensor 72 of a gas generator and an ultraviolet detector 74 or a misfire detector as a detecting means of the engine parameters. When the burner pressure detected by the burner pressure sensor 72 exceeds a specified range, an engine warning alarm is emitted. When the burner pressure sensor 72 is out order, the intensity of ultraviolet rays in an augmenter 30 is detected by the ultraviolet detector 74, whereby misfire is detected by an increase of intensity of ultraviolet rays due to the misfire of combustion in the augmenter 30.

公开(公告)号：JPH11247668A

公开(公告)日：1999-09-14

申请号：JP36489998

申请日：1998-12-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： NIKKANEN JOHN P ,  SANDAHL STEVEN D ,  ZYSMAN STEVEN H

IPC: F02C7/12 ,  F02C7/14 ,  F28D21/00 ,  F28F9/04

Abstract: PROBLEM TO BE SOLVED: To realize excellent engine efficiency and a heat exchanger system by providing an inlet of the heat exchanger system with an inner wall inside in the radial direction of a non-turbulent stream line and disposing an outlet of the heat exchanger system adjacent to the inner wall of a fan duct. SOLUTION: Cooling air always flows from a fan duct partitioned by an inner wall 36 and an outer wall 38 to a heat exchanger 54. The heat exchanger system 52 has an inlet 58 of a low system, and the inlet 58 faces to a fresh air flow. Thus, to minimize the length of the heat exchanger 54, the inlet 58 and the outlet 62 are provided adjacent in the axial direction in the inner wall 36 of the fan duct, whereby even if a disadvantageous static pressure gradient is caused by no turbulence flow in the fan duct between them, cooling air can be let flow through the heat exchanger 54. The inner wall 36 is arranged inside in the radial direction of the inner wall of the fan duct to have exposure ratio of 70% or less, an aspect ratio of 25% or less, and a projection ratio of 10% or less.

公开(公告)号：JPH11247615A

公开(公告)日：1999-09-14

申请号：JP36043198

申请日：1998-12-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WALKER HERBERT L ,  HILTON STEPHEN A ,  BARBIERI JOANN ,  FOURNIER JOHN P ,  TRASK RICHARD D

IPC: F01D5/30 ,  B23K20/12

Abstract: PROBLEM TO BE SOLVED: To provide an improved method for connecting the base part of an airfoil to the disk of the blade integrated rotor assembly of a gas turbine engine. SOLUTION: In this method for connecting the base part 122 of an airfoil 120 to the disk of the blade integrated rotor stage of a gas turbine engine, a slot partitioned by a recessed surface 96 is arranged in the disk provided with a radial outside rim part 46, and the airfoil 120 is used which has a base part having a root part 126 provided with a root part surface 130 and extended in a longitudinal direction. The root part surface 130 and the recessed surface 96 are brought into contact with each other and pressed, and the base part 122 and the rim part 46 are relatively moved, thereby the root part 126 and the recessed surface 96 are substantially brought into contact with each other over the area of the recessed surface 96 during welding. Hereby, a successive linear frictional welding part can be obtained between the base part 122 and the rim part 46.

公开(公告)号：JPH11237048A

公开(公告)日：1999-08-31

申请号：JP35368098

申请日：1998-12-14

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SNYDER TIMOTHY S ,  SOWA WILLIAM A ,  MORFORD STEPHEN A ,  VAN DYKE KEVIN J

IPC: F23R3/30 ,  F23C7/00 ,  F23D14/74 ,  F23D14/82 ,  F23D17/00 ,  F23R3/12 ,  F23R3/28 ,  F23R3/34

Abstract: PROBLEM TO BE SOLVED: To suppress the formation of a nitrogen oxide and at the same time improve the durability of an injector and combustion equipment. SOLUTION: A fuel injector 10 for gas turbine engine includes a scroll 18 where an edge part forms an entrance slot 36, and the slot 36 guides primary combustion air, along a tangential direction, into a mixing room 28 that is bounded by edge plates 14 and 16 being separated from the scroll 18 in the longitudinal direction. A row of fuel injection channels 42 is extended over the length of the slot 36. The injector 10 also includes a center body 48 with a wide tip part 54 for discharging flame. The center body 48 prevents combustion flame from flowing into the mixing room 28 and improves the durability of the combustion equipment 10 by discharging flame when it flows in. Also, by controlling a fuel being discharged through the injection channel 42, the capacity for the center body 48 to discharge flame can be improved and at the same time the flame can be stabilized spatially.

公开(公告)号：JPH11236804A

公开(公告)日：1999-08-31

申请号：JP35696798

申请日：1998-12-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： EL-AINI YEHIA M ,  COWLES BRADFORD A

IPC: F01D5/16 ,  F01D5/10 ,  F01D25/06

Abstract: PROBLEM TO BE SOLVED: To provide a vibration damping device which can be used in a rotor integrally equipped with rotor blades, is effective for periodical push-in actions and aperiodical perturbation, and also is effective for vibration of rotor blade having middle or low grade aspect ratio. SOLUTION: Rotor steps 32 for a gas turbine engine include a rotor disc and a plurality of rotor blades 36. The rotor disc is provided with a hole centering on the axis of rotation and a surface 40 in radial direction on the outside. The rotor blades 36 are extended from the surface 40 in radial direction on the outside to the outside in the radial direction and are distributed around the surface 40. At least one rotor blade 36 is positioned aslant (α) selectively relative to other adjacent rotor blade 36. This slant rotor blade increases the aerodynamic damping of the rotor steps.

公开(公告)号：JPH11236803A

公开(公告)日：1999-08-31

申请号：JP35696698

申请日：1998-12-01

Applicant: UNITED TECHNOLOGIES CORP

Inventor： EL-AINI YEHIA M ,  COWLES BRADFORD A

IPC: F01D5/16 ,  F01D5/10 ,  F01D5/14 ,  F01D5/26 ,  F01D25/06 ,  F04D29/66

Abstract: PROBLEM TO BE SOLVED: To provide a vibration damping device which can be used in a rotor integrally equipped with rotor blades, is effective for periodical push-in actions and aperiodical perturbation, and also is effective for vibration of rotor blade having middle or a low aspect ratio. SOLUTION: Rotor steps 32 for a gas turbine engine include a rotor disc and a plurality of rotor blades 36. The rotor blades 36 are extended from the surface 40 in radial direction on the outside of the rotor disc and are positioned apart at a specified distance 42 from one another. The distance 42 is changed selectively so that the aerodynamic damping of each rotor blade is increased. This selectively changeable inter-blade distance is at least 80% of uniform inter-blade distance.

公开(公告)号：JPH11166637A

公开(公告)日：1999-06-22

申请号：JP25542998

申请日：1998-09-09

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DONNELLY BRIAN G ,  GUKEISEN ROBERT L ,  JENKINS JOHN S

IPC: F01D25/00 ,  F01D17/10 ,  F02C9/18 ,  F04D27/02 ,  F16K1/22

Abstract: PROBLEM TO BE SOLVED: To provide a valve system which can be operated without a union ring, and requirs no operation system. SOLUTION: This is a valve system useful as the bleed valve of a gas turbine engine, in particular. The valve system includes a valve ring or a partition 44 to border a plenum 52. The valve ring has two or more of fluid flow regulation holes 46 of one set, and one or more of chains of a measuring plate 56. Each measuring plate is supported rotatable to one of the holes 46, in order to regulate the fluid flowing through the hole. In a coupling system having a transmission link extending between neighboring measuring plates continuously connects each measuring plates, an operation system to change the rotating movement and the angle from each measuring plate to the measuring plate of the chain includes a driving system responding to an actuator to control the angle of the measuring plate.

公开(公告)号：JPH11156690A

公开(公告)日：1999-06-15

申请号：JP25245798

申请日：1998-09-07

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DANSEREAU RICHARD JAMES ,  TOOHEY EDWARD CHARLES ,  INTERLANDI JOHN SEBASTIAN ,  MEZEI STEVE JOSEPH

IPC: B24B19/14 ,  B23D1/30 ,  B25B5/10 ,  B25B5/14 ,  B25B5/16 ,  B64C3/28 ,  B64F5/00

Abstract: PROBLEM TO BE SOLVED: To precisely form the edge area of an air foil by positioning a tool while the tool is moved in the extended surface of the spanning direction. SOLUTION: During the operation of a device 28 for forming the shape of a front edge, the device 28 is lowered to a position on a fixed air foil. As the device 28 is lowered, the rollers of a roller assembly are engaged with the dented pressure side of the air foil, and these rollers move the device 28 in the chord direction by the compression of one of two springs capable of moving a tool assembly 68 to a coupling assembly 66. A cutting tool 164 is engaged with front edge, the tool 164 is installed and the device 28 is installed in the front edge.

公开(公告)号：JPH11131221A

公开(公告)日：1999-05-18

申请号：JP24545998

申请日：1998-08-31

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MARSZAL DEAN N ,  BEERS RUSSELL A ,  HENDRICKS ROBERT E ,  NOETZEL ALLAN A ,  WRIGHT ROBERT J ,  ERVIN DAVID R ,  SILEO GERARD A

IPC: C23C14/24 ,  C23C14/32 ,  C23C14/56

Abstract: PROBLEM TO BE SOLVED: To provide an efficient gaseous phase deposition forming device capable of continuously applying coating of high quality to many substrates and good in the efficiency of the cost. SOLUTION: A geseous phase deposition forming device for applying substrates with coating is provided, and this device contains plural gaseous phase deposition coaters 14, plural platers 16, a plater docking station 18 and a device for carrying the platers between the coaters and the plater docking station. A shuttle truck connects the plater docking station and coaters. The plater selectively discharged from the coater is carried to the plater docking station along the shuttle truck, where the treated substrate is taken down from the plater, and untreated substrate is placed on the plater.