公开(公告)号：JP2001225411A

公开(公告)日：2001-08-21

申请号：JP2000373775

申请日：2000-12-08

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MALONEY MICHAEL J

IPC: F01D5/28 ,  B32B9/00 ,  B32B15/04 ,  C23C14/06 ,  C23C14/08 ,  C23C14/54 ,  F01D11/08 ,  F02C7/00 ,  F02C7/28

Abstract: PROBLEM TO BE SOLVED: To enhance heat insulating characteristics by correcting the intrinsic heat insulating characteristics of a ceramic coating for heat resistance, that is, the density thereof. SOLUTION: In a method for manufacturing the layered ceramic coating wherein some layers are porous, a heat protecting barrier wall is cyclycally inserted in the gap between a heat source and an evaporation source or external heater under different temperature conditions to be coated with different layers. As coating advances, some layers have a zone I structure and some layers have a zone II structure. In order to increase the porosity of the layers having the zone I structure, heat treatment can be also applied.

公开(公告)号：JP2001207911A

公开(公告)日：2001-08-03

申请号：JP2000396998

申请日：2000-12-27

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GUINAN DANIEL P ,  HUBER DAVID J ,  PERKINS GARY M

IPC: F02C7/00 ,  F02C7/04 ,  F02K3/065 ,  F02K3/077 ,  F04D25/16 ,  F04D29/54

Abstract: PROBLEM TO BE SOLVED: To provide a duct device capable of increasing an air flow rate passing a fan part of a gas turbine engine without increasing a diameter of a fan. SOLUTION: This duct device 10 used in the gas turbine engine 100 having two fans 102, 104 connected to a common shaft includes one primary inlet duct 12 integrated with four primary discharge ducts 14, 16, 18, 20 and two secondary inlet ducts 32, 34 integrated with one secondary discharge duct 36. Each of the ducts includes a port, the ports 38, 40 of the secondary inlet ducts 32, 34 are arranged outside in the radial direction of a port 22 of the primary inlet duct 12 and the ports 24, 26, 28, 30 of the primary discharge ducts 14, 16, 18, 20 are arranged outside in the radial direction of a port 42 of the secondary discharge duct 36.

公开(公告)号：JP2001181767A

公开(公告)日：2001-07-03

申请号：JP2000388095

申请日：2000-12-21

Applicant: UNITED TECHNOLOGIES CORP

Inventor： WATSON THOMAS J

IPC: C22C21/00

Abstract: PROBLEM TO BE SOLVED: To provide an aluminum alloy having excellent mechanical properties at the temperature up to about 300 deg.C. SOLUTION: This aluminum alloy strengthened by high strength dispersion consists of an aluminum solid solution matrix strengthened by the dispersion of particles based on a compound Al3X having an L12 structure. Various alloy elements are used so that the matrix and particles have similar lattice constants, thus the lattice constants of the matrix and particles are modified. The alloy is produced from a melt by rapid solidification.

公开(公告)号：JP2001164902A

公开(公告)日：2001-06-19

申请号：JP37577898

申请日：1998-12-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MARTIN G TABITA ,  JAMES P DOWNES ,  SOECHTING FRIEDRICH O ,  AUXIER THOMAS A

IPC: F01D5/18 ,  F01D9/02

Abstract: PROBLEM TO BE SOLVED: To provide a device to perform proper cooling along the front edge of a hollow airfoil, have a position adapted for a variable stagnation line, generate a cooling airfilm, having uniformity and permanency, in a position situated downstream from the front edges on the two side part of the airfoil and further, minimize a stress generating at the wall of the airfoil. SOLUTION: A hollow airfoil 16 comprises a body; a trench 18; and a plurality of cooling holes 38 formed in the trench. The body is extended in the direction of a chord between a front edge 26 and a rear edge and extended in the direction of a span between an outside radial surface and an inside radial direction and contains an external wall 24 to surround a cavity 22. A trench 18 is situated at an external wall 24 along the front edge 26 and extended in the direction of a span, and aligned with a stagnation line (a stagnation point 42) extending along the front edge 26.

公开(公告)号：JP2001107704A

公开(公告)日：2001-04-17

申请号：JP2000295597

申请日：2000-09-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： LAFLEUR RONALD S

IPC: F01D9/02 ,  F01D5/18

Abstract: PROBLEM TO BE SOLVED: To provide a device and method for cooling a wall, having a selectively adjustable thermal transfer profile so as to be substantially agreed with heat load profile. SOLUTION: A circuit 26 is arranged inside a wall of a gas turbine engine, the circuit 26 having a front end 30, a rear end 32, a first wall part 34, a second wall part 36, and a plurality of pedestals 42, 43, 45. The first and second wall parts 34, 36 spaced certainly from each other are extended between the front end 30 and the rear end 32 of the cooling circuit 26 in the longitudinal direction 52. The pedestals 42, 43, 45 are laid between the first and second wall parts 34 and 36. Characteristics and lines of the pedestals in the cooling circuit 26 are so selected that a thermal transfer cooling profile is provided in the cooling circuit 26 for substantially offsetting heat load profile applied to the wall including the cooling circuit 26.

公开(公告)号：JP2001026299A

公开(公告)日：2001-01-30

申请号：JP2000182396

申请日：2000-06-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYCON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FAANZU KENNETH M ,  FARRELL MARVIN D ,  SANDY DAVID F ,  BEATTY ROBERT D ,  HANSEN BRUCE D

IPC: B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/20 ,  B64C27/33 ,  B64C27/46 ,  B64C27/473 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  F02B75/02 ,  F16C11/06 ,  F16D1/02 ,  F16D1/05 ,  F16D1/06 ,  F16D3/06 ,  F16D3/18 ,  F16D41/07 ,  F16F15/10 ,  F16H1/14 ,  F16H1/22

Abstract: PROBLEM TO BE SOLVED: To provide the optimum design for exercising the optimum performance by providing a bearing bolt connected with a cabin internal bulkhead to be inserted, and a rotatable mounting means by combining an external inner bulkhead, a spherical bearing, a spherical bearing in a bearing cavity, and a bracket. SOLUTION: This snubber assembly comprises a spherical bearing 232, a bearing bolt 234, a fastening nut, a snubber bracket 238 connected and fixed to the spherical bearing 232, and a fixing bolt 240. The combination of the spherical bearing 232 and the snubber bracket 238 is rotatably mounted in a bearing cavity by means of the bearing bolt 234. The bearing bolt 234 is inserted through a bolt hole, the spherical bearing 232 and a bolt hole. The bearing bolt 234 is connected in a rotor hub by the fastening nut and fixed. The fastening nut is engaged with the bearing bolt 234 to keep the stability to the internal bulkhead 223.

公开(公告)号：JP2001018895A

公开(公告)日：2001-01-23

申请号：JP2000182397

申请日：2000-06-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： CYCON JAMES P ,  HUNTER DAVID H ,  KOHLHEPP FRED W ,  KRAUSS TIMOTHY A ,  MILLEA VINCENT F ,  FAANZU KENNETH M ,  FARRELL MARVIN D ,  SANDY DAVID F ,  BEATTY ROBERT D ,  HANSEN BRUCE D

IPC: B64C27/10 ,  B64C27/12 ,  B64C27/14 ,  B64C27/20 ,  B64C27/33 ,  B64C27/46 ,  B64C27/473 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  F02B75/02 ,  F16C11/06 ,  F16D1/02 ,  F16D1/05 ,  F16D1/06 ,  F16D3/06 ,  F16D3/18 ,  F16D41/07 ,  F16F15/10 ,  F16H1/14 ,  F16H1/22

Abstract: PROBLEM TO BE SOLVED: To provide a rotor type UAV used for a reconnaissance flight and a communication mission over a wide area, especially for a strategic reconnaissance flight. SOLUTION: A unmanned aerial vehicle(UAV) 10 has a complex circular body structure 20 surrounding a rotor assembly 100 including a pair of coaxial multi-blade counter-rotating rotors. The circular body structure 20 includes a circular C-shape structure. The circular C-shape structure defines a detachable panel structure mounted with a combination of a cavity and the circular C-shape structure. The UAV has a drive train assembly having a sprag clutch, an engine coupled subassembly, transmission coupled subassembly, and a drive shaft.

公开(公告)号：JP2000345315A

公开(公告)日：2000-12-12

申请号：JP2000115748

申请日：2000-04-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： EATON HARRY E ,  LAWTON THOMAS H

IPC: B05D3/02 ,  B05D7/14 ,  B05D7/24 ,  B32B37/00 ,  C04B41/50 ,  C04B41/52 ,  C04B41/85 ,  C04B41/87 ,  C04B41/89 ,  C23C4/02 ,  C23C4/06 ,  C23C4/10 ,  C23C4/18 ,  C23C28/00 ,  C23C28/04 ,  F01D5/28

Abstract: PROBLEM TO BE SOLVED: To provide a method for producing a silicon-contg. substrate-contg. article free from cracks and capable of preventing the formation of a gaseous compd. of Si in a high temp. environment in which moisture is present. SOLUTION: A silicon-contg. substrate is heated to about >=1100 deg.C, and a barrier layer composed of barium-strontium aluminosilicate is formed at the same temp. to prepare a substrate applied with the coating, and next, the substrate applied with the coating is held at the same temp. for about >=15 min. By this holding, the barrier layer changes from the amorphous structure to the crystal one. The thermal expansion coefficient of the barrier layer is ±0.5 ppm/ deg.C of that of the substrate.

公开(公告)号：JP2000220472A

公开(公告)日：2000-08-08

申请号：JP36411499

申请日：1999-12-22

Applicant: UNITED TECHNOLOGIES CORP

Inventor： DUYN KEVEN G VAN

IPC: F02C7/00 ,  F01D11/12 ,  F01D21/04 ,  F01D25/24

Abstract: PROBLEM TO BE SOLVED: To reduce the damage of a fan case and a support structure in the breakage of a fan blade by determining a radial mutual interference zone having a boundary determined on the outside by the surface of the hard metal of the fan case, and arranging a hardened liner in this zone. SOLUTION: An axial turbo fan gas turbine engine 10 comprises a fan section 14, a compressor section 16, a combustor section 18, and a turbine section 20 which are coaxially arranged. The fan section 14 has a stator assembly 27 and a rotor assembly 28. The stator assembly 27 has a fan containment case assembly 30 for forming the outside wall of a secondary passage 24. In this case, a segmented fan case liner consisting of a hardened material is arranged in the mutual interference zone to which the outer edge of a rotor blade 34 opposes within the assembly 30 to improve the reliability in the damage of the rotor blade.

公开(公告)号：JP2000197957A

公开(公告)日：2000-07-18

申请号：JP36051899

申请日：1999-12-20

Applicant: UNITED TECHNOLOGIES CORP

Inventor： SCHIRRA JOHN J ,  ANDERSON DAVID WILLIAM ,  MARCIN JOHN JOSEPH JR ,  PRIVITZER EBERHART ,  SAMUELSON JEFFERY WILLIAM ,  TU JOHN SIUMING

IPC: B22D17/20

Abstract: PROBLEM TO BE SOLVED: To execute die casting a member having high m.p. in a good condition by selecting the ratio of the inside diameter and the outside diameter of a sleeve so as to minimize the thermal deformation of the sleeve in the case of pouring molten material into the shot sleeve. SOLUTION: The cylindrical sleeve has the inside diameter Ri and the outside diameter Ro in the cold state, and as the molten material is poured into a low portion, the low portion is expanded more than the portion at the upper side and deformed as shown with the broken line to form an elliptic shape shown with a major axis Ma and a minor axis Mm. In such a case, the ratio (Ro/Ri) of the outside diameter and the inside diameter is desirable to be at least 1.5. In this way, the molten material having suitable volume, (particularly, in the case of filling only a small portion of the molten material), is formed as bow shape in the longitudinal direction or formed as the elliptic shape, and it can be sufficiently minimized that the sleeve is thermally deformed and the machine can be prevented from jamming. further, the inside diameter is desirable to be at least 1.5 inch.