Abstract: It is prevented of degradation of communication quality caused by estimation errors of plural path differences between plural antennas for feeder link (FL antennas) incorporated in an aerial-staying type communication relay apparatus and plural gateway (GW) stations.

Abstract: It is prevented of degradation of communication quality caused by estimation errors of plural path differences between plural antennas for feeder link (FL antennas) incorporated in an aerial-staying type communication relay apparatus and plural gateway (GW) stations.

Abstract: A gas turbine engine according to one aspect of the present invention includes: an oil tank storing lubricating oil; and a cylindrical external case accommodating a compressor, a combustor, and a turbine. The oil tank is arranged along an outer peripheral surface of the external case so as to surround the external case.

Abstract: A gas turbine engine including a compressor that compresses air taken in; a combustor that sprays a fuel into the compressed air and combusts the fuel; a turbine rotated by energy of the combustion gas generated by the combustor; a rotating shaft coupling the compressor and the turbine; a rear bearing that is a cageless ball bearing including an inner race, an outer race, and a ball, the inner race being fixed to a portion of the rotating shaft which portion is close to the turbine; a housing to which the rear bearing is attached; and a rear bearing holding member that is interposed between the rear bearing and the housing and holds the outer race of the rear bearing such that the outer race of the rear bearing is movable in an axial direction relative to the housing.

Abstract: An additive manufactured object is a stack including a first metal layer made of a first metallic material and a second metal layer that includes second dot beads made of a second metallic material. The additive manufactured object includes an intermediate layer between the first and second metal layers. The intermediate layer includes a first structural part as a structure made of the first metallic material and a second structural part as a structure made of the second metallic material. The first and second structural parts engage each other in a unit structure, and an arrangement of the unit structures arranged in the intermediate layer has translational symmetry in a plane perpendicular to a stacked direction of the first and second metal layers. The intermediate layer includes, at a junction interface between the first and the second structural parts, an intermetallic compound layer including an intermetallic compound.

Abstract: An oil supply device of an aircraft gas turbine includes: a lubrication extraction pipe including a first end and a second end, the first end communicating with a compressor of the gas turbine, an ejection port being provided at the second end and directed to a lubricated member; an oil tank configured to store oil; an oil pipe including a first end and a second end, the first end communicating with the oil tank, the second end communicating with the lubrication extraction pipe; and an electric pump interposed on a portion of the oil pipe and configured to suck the oil from the oil tank and supply the oil to an inside of the lubrication extraction pipe.

Abstract: A downlink interference is dynamically suppressed in a multi-feeder link of a same frequency between an aerial-floating type communication relay apparatus and plural gateway (GW) stations with a simple configuration.

Abstract: Interferences in multi-feeder links on a same frequency between an aerial-floating type communication relay apparatus and plural gateway (GW) stations are dynamically suppressed. Each of the plural GW stations transmits plural pilot signals with frequencies different from each other in the feeder link.

Abstract: A gas turbine engine includes: a fan that is in front of a compressor and rotates in association with a rotating shaft; a casing including an inner shell and an outer shell and a bypass passage; bearings inside the inner shell; an oil mist generator that is outside the outer shell and generates oil mist by mixing oil with compressed air extracted through an extraction port of the compressor; an air pipe through which the compressed air extracted from the compressor is guided to the oil mist generator; and an oil mist pipe through which the oil mist generated by the oil mist generator is guided to the bearings. At least one of the air pipe and the oil mist pipe includes a heat exchanger that is in the bypass passage and is cooled by the air flowing through the bypass passage.

Abstract: A gas turbine engine includes: a casing that accommodates a compressor and the like; bearings; a main lubricator including an oil mist generator that generates oil mist by mixing oil with compressed air extracted from the compressor and a first supply passage through which the oil mist is guided to the bearings; and a starting lubricator including a second supply passage through which a gas flowing out from a gas source is guided to a connection portion of the first supply passage, the connection portion being connected to the second supply passage, and an opener that starts supply of the gas from the gas source. The main lubricator supplies the oil mist to the bearings through the first supply passage by the pressure of the compressed air extracted from the compressor. When the opener starts the supply of the gas, the starting lubricator supplies the oil mist to the bearings by the pressure of the gas flowing out from the gas source.

Abstract: Provided is a gas turbine engine including a main passage through which compressed air extracted from a compressor is guided to a bearing; and an oil supply device that supplies oil to the main passage. The oil supply device includes a pressure reducer in the main passage; an oil tank a divider that is movable and divides an internal space of the container into an oil chamber storing the oil and an air chamber; an extruder including a cylinder and a piston that divides an internal space of the cylinder into a first chamber and a second chamber; a switching mechanism that switches between a first state where the first chamber communicates with a low-pressure space whose pressure is lower than pressure in the air chamber and a second state where the first chamber communicates with a high-pressure space whose pressure is higher than pressure in the downstream passage.

Abstract: A gas turbine engine includes: a main passage through which compressed air extracted from a compressor is guided to a bearing; and an oil supply device that includes an oil tank storing oil and supplies the oil to the main passage through which the compressed air flows to generate oil mist. The oil supply device includes: a pressure reducer disposed at the main passage; a bypass passage that bypasses the pressure reducer and connects an upstream passage and a downstream passage; a holding chamber disposed at the bypass passage and having a predetermined volume; a switching mechanism that permits or blocks communication between the holding chamber and the oil tank, communication between the holding chamber and the upstream passage, and communication between the holding chamber and the downstream passage; and a controller that controls the switching mechanism.

Abstract: It is dynamically suppressed of a downlink interference in a reverse link of a multi-feeder link of a same frequency between an aerial-staying type communication relay apparatus and plural gateway (GW) stations. A relay communication station of the communication relay apparatus estimates plural propagation path responses respectively between plural GW stations and an antenna for feeder link of the communication relay apparatus based on reception results of plural pilot signals received from each of plural GW stations. The relay communication station calculates a weight for suppressing an interference signal that causes an interference by a transmission signal transmitted from a relay communication station to the GW station and received by another GW station, based on the plural propagation path responses, with respect to each of the plural GW stations.

Abstract: Interference in multi-feeder links of a same frequency between an aerial-floating type communication relay apparatus and plural gateway (GW) stations is suppressed. A transmission signal band of a feeder link is divided into plural divided frequency bands, and plural propagation path responses between plural GW stations and an antenna for feeder link of the communication relay apparatus are respectively estimated with respect to each of plural divided frequency bands, by setting a center frequency of the divided frequency band as an estimation frequency, based on a reception result of the pilot signals respectively received from the plural GW stations and separated from each other. A weight for suppressing an interference signal that causes an interference by a transmission signal transmitted from the GW station and received with a directional beam corresponding to another GW station is calculated for each of the divided frequency bands based on the plural propagation path responses.

Abstract: While suppressing a power consumption of an aerial-floating type communication relay apparatus, an interference in a multi-feeder link of a same frequency between the communication relay apparatus and plural gateway (GW) stations is suppressed. A relay communication station of the communication relay apparatus performs a first interference suppression process and a second interference suppression process by switching therebetween. The first interference suppression process suppresses an interference signal that causes an interference by a transmission signal transmitted from a gateway station and received with a directional beam corresponding to another gateway station, by using a propagation path response estimated with one frequency in a transmission signal band as an estimation frequency based on a reception result of a pilot signal without dividing a transmission signal band of a feeder link.

Abstract: A gas turbine engine including a compressor that compresses air taken in; a combustor that sprays a fuel into the compressed air and combusts the fuel; a turbine rotated by energy of the combustion gas generated by the combustor; a rotating shaft coupling the compressor and the turbine; a rear bearing that is a cageless ball bearing including an inner race, an outer race, and a ball, the inner race being fixed to a portion of the rotating shaft which portion is close to the turbine; a housing to which the rear bearing is attached; and a rear bearing holding member that is interposed between the rear bearing and the housing and holds the outer race of the rear bearing such that the outer race of the rear bearing is movable in an axial direction relative to the housing.

Abstract: A gas turbine engine according to one aspect of the present invention includes: an oil tank storing lubricating oil; and a cylindrical external case accommodating a compressor, a combustor, and a turbine. The oil tank is arranged along an outer peripheral surface of the external case so as to surround the external case.

Abstract: A downlink interference is dynamically suppressed in a multi-feeder link of a same frequency between an aerial-floating type communication relay apparatus and plural gateway (GW) stations with a simple configuration.

Abstract: A gas turbine engine includes: a main passage through which compressed air extracted from a compressor is guided to a bearing; and an oil supply device that includes an oil tank storing oil and supplies the oil to the main passage through which the compressed air flows to generate oil mist. The oil supply device includes: a pressure reducer disposed at the main passage; a bypass passage that bypasses the pressure reducer and connects an upstream passage and a downstream passage; a holding chamber disposed at the bypass passage and having a predetermined volume; a switching mechanism that permits or blocks communication between the holding chamber and the oil tank, communication between the holding chamber and the upstream passage, and communication between the holding chamber and the downstream passage; and a controller that controls the switching mechanism.

Abstract: Provided is a gas turbine engine including a main passage through which compressed air extracted from a compressor is guided to a bearing; and an oil supply device that supplies oil to the main passage. The oil supply device includes a pressure reducer in the main passage; an oil tank a divider that is movable and divides an internal space of the container into an oil chamber storing the oil and an air chamber; an extruder including a cylinder and a piston that divides an internal space of the cylinder into a first chamber and a second chamber; a switching mechanism that switches between a first state where the first chamber communicates with a low-pressure space whose pressure is lower than pressure in the air chamber and a second state where the first chamber communicates with a high-pressure space whose pressure is higher than pressure in the downstream passage.