公开(公告)号：US20190277201A1

公开(公告)日：2019-09-12

申请号：US15918097

申请日：2018-03-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Leo J. Veilleux, JR. ,  Lubomir A. Ribarov

IPC: F02C9/28 ,  B64D37/32 ,  F02C7/232 ,  F01P3/00

Abstract: A fuel-based thermal management system may comprise a heat exchanger configured to thermally couple a fluid and a fuel. A controller may be configured to modulate a flow of the fluid to the heat exchanger. A tangible, non-transitory memory may be configured to communicate with the controller. The controller may determine a temperature of the fluid, estimate a dissolved oxygen concentration in the fuel using a first fuel temperature, a flight cycle time, and at least one of an altitude measurement or a ambient pressure measurement, and modulate the flow of the fluid to the heat exchanger based on the dissolved oxygen concentration.

公开(公告)号：US20150284071A1

公开(公告)日：2015-10-08

申请号：US14578975

申请日：2014-12-22

Applicant: United Technologies Corporation

Inventor： Leo J. Veilleux, JR. ,  Lubomir A. Ribarov

IPC: B64C11/48

CPC classification number: B64C11/48 ,  B64D27/14 ,  B64D35/06 ,  B64D35/08 ,  B64D2027/005

Abstract: A disclosed aircraft propulsion system includes a gas turbine engine supported within an aircraft fuselage, a main drive driven by the gas turbine engine and an open rotor propeller system supported outside of the aircraft fuselage separately from the gas turbine engine. A secondary drive that is driven by the main drive drives the open rotor propeller system.

Abstract translation: 所公开的飞机推进系统包括支撑在飞行器机身内的燃气涡轮发动机，由燃气涡轮发动机驱动的主驱动器和与燃气涡轮发动机分开地支撑在飞机机身外部的开放式转子螺旋桨系统。 由主驱动器驱动的副驱动器驱动开式转子螺旋桨系统。

公开(公告)号：US20190292932A1

公开(公告)日：2019-09-26

申请号：US15933668

申请日：2018-03-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Leo J. Veilleux, JR. ,  Thomas O. Harris ,  Lubomir A. Ribarov

IPC: F01D11/22 ,  B64D31/00 ,  F01D15/02 ,  F02C7/28

Abstract: An objective-driven system for blade tip clearance control may comprise a BOAS and a controller in operable communication with the BOAS. A tangible, non-transitory memory may be configured to communicate with the controller, the tangible, non-transitory memory may have instructions stored thereon that, in response to execution by the controller, cause the controller to perform operations comprising receiving an operating objective definition, and modulating a location of the BOAS using an optimization loop comprising the operating objective definition, input vector variables, and output vector variables driven by the input vector variables.

公开(公告)号：US20160312703A1

公开(公告)日：2016-10-27

申请号：US15105385

申请日：2014-11-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Lubomir A. Ribarov ,  Leo J. Veilleux, JR. ,  James S. Elder, JR.

IPC: F02C7/18 ,  F04D29/32 ,  F01D15/00 ,  F02C9/18 ,  F02C7/14 ,  F02C7/22

CPC classification number: F02C7/18 ,  F01D11/24 ,  F01D15/005 ,  F01D25/12 ,  F02C7/14 ,  F02C7/222 ,  F02C9/18 ,  F04D29/321 ,  F05D2220/32 ,  F05D2240/307 ,  F05D2260/213 ,  Y02T50/671 ,  Y02T50/676

Abstract: In accordance with at least one aspect of this disclosure, a turbomachine cooling system includes a first low pressure port disposed in a low pressure portion of a turbomachine and a first high pressure port disposed in a high pressure portion of the turbomachine and in selective fluid communication with the first low pressure port via a cooling channel. The high pressure portion of the turbomachine is configured for a higher compression than the low pressure portion of the turbomachine where the first low pressure port is disposed. The cooling system can include a heat exchanger system disposed in the cooling channel such that a flow traveling from the first high pressure port to the first low pressure port is cooled by the heat exchanger system before traveling through the first low pressure port into the low pressure portion of the turbomachine.

Abstract translation: 根据本公开的至少一个方面，涡轮机冷却系统包括设置在涡轮机的低压部分中的第一低压端口和设置在涡轮机的高压部分中并且在选择性流体连通中的第一高压端口 通过冷却通道与第一低压端口连接。 涡轮机的高压部分构造成比设置有第一低压端口的涡轮机的低压部分更高的压缩。 冷却系统可以包括设置在冷却通道中的热交换器系统，使得从第一高压端口运动到第一低压端口的流量在通过第一低压端口进入低压之前被热交换器系统冷却 涡轮机的一部分。

公开(公告)号：US20160312645A1

公开(公告)日：2016-10-27

申请号：US15105358

申请日：2014-12-01

Applicant: United Technologies Corporation

Inventor： Lubomir A. Ribarov ,  Leo J. Veilleux, JR. ,  James S. Elder, JR.

IPC: F01D11/20 ,  F01D25/24 ,  F01D5/12

CPC classification number: F01D11/20 ,  F01D5/12 ,  F01D11/22 ,  F01D25/24 ,  F05D2220/30 ,  F05D2240/307 ,  F05D2260/57

Abstract: A turbomachine blade clearance system can include an actuator having an anchor portion for fixation to an interior surface of a turbomachine housing and an actuating portion for actuating movement relative to the anchor portion. A turbomachine blade seal can be operatively connected to the actuating portion of the actuator and configured to move relative to the turbomachine housing to adjust a distance from a turbomachine blade of a turbomachine to maintain a predetermined gap clearance between the blade seal and the blade.

Abstract translation: 涡轮机叶片间隙系统可以包括具有用于固定到涡轮机壳体的内表面的锚定部分的致动器和用于致动相对于锚定部分的运动的致动部分。 涡轮机叶片密封件可以可操作地连接到致动器的致动部分并且被构造成相对于涡轮机壳体移动以调节与涡轮机的涡轮机叶片的距离，以保持叶片密封件和叶片之间的预定的间隙。