Hartford, CT, United States
Hartford, CT, United States

United Technologies Corporation is an American multinational conglomerate headquartered in the United Technologies Building in Hartford, Connecticut. It researches, develops, and manufactures high-technology products in numerous areas, including aircraft engines, helicopters, HVAC, fuel cells, elevators and escalators, fire and security, building systems, and industrial products, among others. UTC is also a large military contractor, producing missile systems and military helicopters, most notably the UH-60 Black Hawk helicopter. Gregory Hayes is the current CEO. Wikipedia.


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Patent
United Technologies | Date: 2017-01-27

A method of managing a gas turbine engine variable area fan nozzle includes the steps of operating a variable area fan nozzle according to a first operating schedule. An icing condition input is evaluated to determine the likelihood of ice presence. The first operating schedule is altered to provide a variable area fan nozzle position if ice is likely present or actually present to provide an icing operating schedule different than the first operating schedule. The first operating schedule corresponds to the flaps at least partially open at air speeds below a first airspeed. The altering step includes closing the flaps below the first airspeed as part of the icing operating schedule. The variable area fan nozzle position is adjusted according to the icing operating schedule. A fan is arranged in a fan nacelle that includes a flap configured to be movable between first and second positions. An actuator is operatively coupled to the flap.


Patent
United Technologies | Date: 2017-01-31

A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.


Patent
United Technologies | Date: 2017-05-17

An airfoil (201) of a gas turbine engine (20) is provided. The airfoil includes an airfoil body (209) having at least one internal flow passage (218), the body having a first surface (214) and a second surface (216), the first surface defining a wall of the at least one internal flow passage and a bleed port (219) fluidly connecting the at least one internal flow passage to the second surface. The bleed port includes a bleed orifice (220) extending from the second surface toward the internal flow passage and a bleed port cavity (226) extending from the first surface toward the second surface, the bleed port cavity and the bleed orifice fluidly connected. The bleed port cavity is defined by a bleed port cavity wall and a base wall surrounding the bleed orifice. The bleed port cavity wall extends from the first surface to the base wall.


Patent
United Technologies | Date: 2017-04-26

A drainage assembly (68) includes a first segment (70A) with a first inner tube (76A) defining a first inner tube passage (78A), a first outer tube (72A) concentrically disposed around the first inner tube (76A) and defining a first outer tube passage (74A), and a first fitting (80A) disposed on an end of the first segment (70A). The first fitting (80A) has a first inner passage (82A) in fluid communication with the first inner tube passage (78A) and a first outer passage (84A) in fluid communication with the first outer tube passage (74A). A plate (88) is positioned adjacent the first fitting (80A). The plate (88) has a second inner passage (90) in fluid communication with the first inner passage (82A) on one side, and a second outer passage (92) in fluid communication with the first outer passage (84A) on the one side. Also included is a drainage line (104) in fluid communication with the first outer tube passage (74A).


Patent
United Technologies | Date: 2017-01-11

An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10 to 20 in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span.


Patent
United Technologies | Date: 2017-02-15

A method of additive manufacturing comprises determining a first resonant frequency of an unflawed reference workpiece at a first partial stage of completion, fabricating a production workpiece to the first partial stage of completion via additive manufacture, sensing a second resonant frequency of the production workpiece in-situ at the first partial stage of completion, during the fabrication, analyzing the workpiece for flaws based on comparison of the first and second resonant frequencies, and providing an output indicative of production workpiece condition, based on the analysis. An additive manufacturing system comprises an additive manufacturing tool, a sensor, and a controller. The additive manufacturing tool is disposed to construct a workpiece via iterative layer deposition. The sensor is disposed to determine a resonant frequency of the workpiece in-situ at the additive manufacturing tool, during fabrication. The controller is configured to terminate manufacture of the workpiece if the resonant frequency differs substantially from a reference frequency.


Patent
United Technologies | Date: 2016-12-28

An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential leading edge location and a span position that corresponds to a curve that is at least a third order polynomial with a generally S-shaped curve that has an initial negative slope followed by a positive slope and then a second negative slope. The positive slope leans toward the suction side and the negative slopes lean toward the pressure side.


Patent
United Technologies | Date: 2017-05-31

A method of real-time oil consumption is disclosed. A method of real-time oil consumption detection may comprise capturing a raw oil quantity (310), calculating a corrected oil quantity (330), calculating a predicted oil quantity, calculating a prediction error (350), and calculating an estimated oil consumption rate. Raw oil quantity (310) may be captured from an oil quantity sensor (235) in an engine. Corrected oil quantity (330) may be calculated by taking raw oil quantity (310) and applying environmental and engine operational conditions. Prediction error (350) may be calculated by finding the difference between corrected oil quantity and predicted oil quantity (330). Oil consumption rate may be calculated by applying a regression algorithm to prediction error (350).


Patent
United Technologies | Date: 2017-05-31

The present disclosure provides methods, systems, and computer-readable media for the fault detection and identification in an aircraft that may occur in real time during a flight, or any time the aircraft is operating. For example, a controller (250) may receive and calculate various parameter values at various times during an aircraft flight, and compare those values to baseline values (261, 266) in order to determine if a fault has occurred. Additionally, the controller (250) may identify a fault that has occurred by comparing a calculated fault signature value with a fault signature database (280) comprising fault signatures and their associated faults.


Grant
Agency: European Commission | Branch: H2020 | Program: RIA | Phase: DS-01-2016 | Award Amount: 5.42M | Year: 2017

The main objective of the ANASTACIA is to address the constant discovery of vulnerabilities in ICT components providing assurance that ICT systems are secure and trustworthy by design. To this end, ANASTACIA will research and develop a holistic security framework, which will address all the phases of the ICT Systems Development Lifecycle and will be able to take autonomous decisions using new networking technologies (SDN/NFV), and dynamic security enforcement and monitoring methodologies and tools. The ANASTACIA framework will include a comprehensive suite of tools and enablers: - A security development paradigm based on the compliance to security best practices and the use of the security components and enablers. - A suite of distributed trust and security components and enablers, able to dynamically orchestrate and deploy user security policies and actions within complex and dynamic CPS and IoT architectures. - Online monitoring and testing techniques that will allow more automated adaptation of the system to mitigate new and unexpected security vulnerabilities. - A holistic Dynamic Security and Privacy Seal, combining security and privacy standards and real time monitoring and online testing. This will provide quantitative and qualitative run-time evaluation of privacy risks and security levels, which can be easily understood and controlled by the final users. ANASTACIA results will be driven and demonstrated in three high impact Use Cases: Mobile Edge Computing, Smart Building and IoT networks. Bringing together leading partners with wide-ranging expertise, the ANASTACIA Consortium will combine the philosophy and business models of communication technologies with inherently integrated security and privacy solutions, creating a security framework where the end users will be able to control their security and privacy policies enforcement, and application developers, in particular SMEs, will find an open and sustainable ecosystem for secure SLCD.

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