公开(公告)号：US11192655B2

公开(公告)日：2021-12-07

申请号：US15802947

申请日：2017-11-03

Applicant: Hamilton Sundstrand Corporation

Inventor： Louis J. Bruno ,  Thomas M. Zywiak

IPC: B64D13/08 ,  B64D13/06 ,  B64D13/02

Abstract: An environmental control system of an aircraft includes a ram air circuit with a ram air shell having at least one heat exchanger positioned therein, a dehumidification system arranged in fluid communication with the ram air circuit, a compression device arranged in fluid communication with the ram air circuit and the at least one dehumidification system, and an expansion device arranged in fluid communication with the ram air circuit. At least one of the compression device and the expansion device is selectively operable to supplement the ram air within the ram air circuit to meet a demand of the aircraft.

公开(公告)号：US20210354832A1

公开(公告)日：2021-11-18

申请号：US17388568

申请日：2021-07-29

Applicant: Hamilton Sundstrand Corporation

Inventor： Louis J. Bruno

IPC: B64D13/06

Abstract: A method of operating an environmental control system of an aircraft includes providing a first medium to the environmental control system including a compressor and a turbine. The first medium is provided to the compressor and the turbine sequentially. A second medium is provided to the environmental control system. In a first mode of operation, the first medium and the second medium mix within the turbine and in a second mode of operation the second medium bypasses the turbine such that the first medium and the second medium mix downstream from the turbine.

公开(公告)号：US11104442B2

公开(公告)日：2021-08-31

申请号：US16358267

申请日：2019-03-19

Applicant: Hamilton Sundstrand Corporation

Inventor： Louis J. Bruno

IPC: B64D13/06

Abstract: An environmental control system of an aircraft includes a compressing device having a compressor configured to receive a flow of a first medium and a turbine configured to receive the flow of the first medium from the compressor and a flow of a second medium. The turbine is arranged downstream from the compressor along a flow path of the first medium. A dehumidification system is arranged in fluid communication with the turbine and a bypass valve is operable configured to divert the flow of the first medium around the turbine and at least a portion of the dehumidification system.

公开(公告)号：US20210047044A1

公开(公告)日：2021-02-18

申请号：US17089107

申请日：2020-11-04

Applicant: Hamilton Sundstrand Corporation

Inventor： Louis J. Bruno ,  Harold W. Hipsky

IPC: B64D13/02

Abstract: A compressing device includes a first turbine a second turbine and a compressor. The first turbine is configured to provide a first energy by expanding a first medium and the second turbine configured to provide a second energy by expanding a second medium. The compressor is configured to receive the first energy and the second energy during a first mode of the compressing device, receive the first energy during a second mode of the compressing device, and compress the second medium in accordance with the first mode or the second mode.

公开(公告)号：US20210001992A1

公开(公告)日：2021-01-07

申请号：US16459152

申请日：2019-07-01

Applicant: Hamilton Sundstrand Corporation

Inventor： Tony Ho ,  Louis J. Bruno

IPC: B64D13/06 ,  F25B9/00 ,  F25B9/06

Abstract: An environmental control system for providing a conditioned medium to one or more loads of an aircraft includes a compressing device including a compressor and a turbine operably coupled to the compressor. The turbine is arranged downstream from the compressor relative to a flow of first medium. At least one power turbine is operably coupled to the compressor. The at least one power turbine is configured to receive a flow of a second medium, and the flow of second medium includes a cabin discharge air.

公开(公告)号：US10830133B2

公开(公告)日：2020-11-10

申请号：US14755929

申请日：2015-06-30

Applicant: Hamilton Sundstrand Corporation

Inventor： Louis J. Bruno ,  Thomas M. Zywiak

IPC: F02C6/08 ,  B64D13/06

Abstract: An engine compressor bleed system of an engine for an aircraft is provided including a plurality of compressor pressure ports configured to supply bleed air to satisfy a cooling load for at least a first stage of a flight profile of an aircraft. A first pressure port of the plurality of compressor pressure ports is configured to provide bleed air having a pressure at least equal to a cabin pressure of an aircraft and a temperature that does not exceed a predetermined threshold.

公开(公告)号：US10597162B2

公开(公告)日：2020-03-24

申请号：US15604510

申请日：2017-05-24

Applicant: Hamilton Sundstrand Corporation

Inventor： Louis J. Bruno ,  Harold W. Hipsky

IPC: B64D13/08 ,  B64D13/02 ,  B64D13/06 ,  F01D5/06 ,  F01D17/10 ,  F04D25/04 ,  F04D29/58

Abstract: An airplane is provided. The airplane includes a first medium, a second medium, and an air conditioning. The air conditioning system includes a first turbine, a compressor, and a mixing point. The compressor is located upstream of the turbine in a flow path of the first medium. The mixing point is a location at which the first medium mixes with the second medium. The mixing point is downstream of the compressor and upstream of the turbine.

公开(公告)号：US20190300179A1

公开(公告)日：2019-10-03

申请号：US16447341

申请日：2019-06-20

Applicant: Hamilton Sundstrand Corporation

Inventor： Louis J. Bruno

IPC: B64D13/06 ,  B64D13/08

Abstract: An airplane is provided. The airplane includes an environmental control system that provides a pressurized medium to a chamber of the airplane. The airplane also includes a bleed system. The bleed system includes a plurality of ports, each of which can provide a bleed medium from an engine of the airplane to the environmental control system. The plurality of ports includes at least a first port, a second port, and a third port. The first port is selected for an idle condition. The second port is selected for a hot day cruise condition. The third port is selected for a standard operating condition. The bleed system can operate in a first mode, a second mode, or a third mode to provide the bleed medium to the environmental control system from the first port, the second port, or the third port respectively.

公开(公告)号：US20190225343A1

公开(公告)日：2019-07-25

申请号：US15987590

申请日：2018-05-23

Applicant: Hamilton Sundstrand Corporation

Inventor： Louis J. Bruno ,  Thomas M. Zywiak

IPC: B64D13/06

Abstract: An environmental control system of an aircraft includes a ram air circuit including a ram air shell having at least one heat exchanger positioned therein, a dehumidification system arranged in fluid communication with the ram air circuit, and a compressing device arranged in fluid communication with the ram air circuit and the dehumidification system. The compression device includes a compressor and a first turbine coupled to one another via a shaft. During operation of the first turbine, work is extracted from a first medium within the first turbine to power the compressor. At an outlet of the first turbine, a temperature of the first medium is above freezing and at least a portion of the moisture within the first medium is condensed.

公开(公告)号：US10309303B2

公开(公告)日：2019-06-04

申请号：US15236085

申请日：2016-08-12

Applicant: Hamilton Sundstrand Corporation

Inventor： Robert A. Bayles ,  Todd A. Spierling ,  Louis J. Bruno ,  Harold W. Hipsky

IPC: F02C6/00 ,  F02C6/08 ,  F01D15/10 ,  F02C3/04 ,  H02K7/18 ,  F02C7/32

Abstract: A generator arrangement includes a generator and a pneumatic turbine. The pneumatic turbine is operably connected to the generator. A gas turbine engine compressor section is in fluid communication with the pneumatic turbine through a bleed air conduit to provide pressurized air to the pneumatic turbine for applying mechanical rotation to the generator.