1
Robert W Paterson, Walter M Presz Jr, Bruce L Morin: Mixer ejector flow distributor. Carrier Corporation, July 27, 1993: US05230656 (25 worldwide citation)

An apparatus for attaining improved flow uniformity through and at the exit of an air duct by mixing and distributing the air flow. The apparatus has a wall containing a plurality of convoluted corrugations or lobes arranged in conjunction with an airfoil shaped faired body to form an ejector passag ...


2
Bruce L Morin, Detlef Korte: Low noise turbine for geared turbofan engine. United Technologies Corporation, MTU Aero Engines, Carlson Gaskey & Olds PC, August 21, 2012: US08246292 (21 worldwide citation)

A gas turbine engine is utilized in combination with a gear reduction to reduce the speed of a fan relative to a low pressure turbine speed. The gas turbine engine is designed such that a blade count in the low pressure turbine multiplied by the speed of the low pressure turbine will result in opera ...


3
Bruce L Morin, Rudolph A Ksiazkiewicz Jr, Dennis Cicon: Micro-perforated acoustic liner. United Technologies Corporation, Carlson Gaskey & Olds, June 2, 2009: US07540354 (15 worldwide citation)

An example liner assembly includes a backing plate that supports a cellular structure covered by a perforated face sheet including a plurality of openings. Each of the plurality of openings is of a size determined to provide desired acoustic performance.


4
Ramons A Reba, Bruce L Morin, Stephen A Morford, Wesley K Lord: Airfoil acoustic impedance control. United Technologies Corporation, Kinney & Lange P A, October 27, 2009: US07607287 (13 worldwide citation)

A noise control cassette for a gas turbine engine includes a perforated face sheet configured for exposure to an airflow, a non-perforated backing sheet, a core arranged between the face sheet and the backing sheet and defining a cavity between the face sheet and the backing sheet having an effectiv ...


5
David A Topol, Bruce L Morin: Low noise compressor rotor for geared turbofan engine. United Technoloiies Corporation, Carlson Gaskey & Olds PC, September 16, 2014: US08834099 (12 worldwide citation)

A gas turbine engine comprises a fan and a turbine section having a first turbine rotor. The first turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from a fan drive turbine rotor. The compressor rotor has a number of com ...


6
Dilip Prasad, Bruce L Morin, Wesley K Lord, Douglas C Mathews: Airfoil surface impedance modification for noise reduction in turbofan engines. United Technologies Corporation, Bachman & LaPointe P C, March 28, 2006: US07018172 (11 worldwide citation)

In accordance with the present invention, an aircraft engine is provided with a component which helps reduce the noise generated by the engine. The component has a first aerodynamic surface, a second aerodynamic surface, and a system for reducing noise without altering a pressure differential betwee ...


7
David A Topol, Bruce L Morin: Low noise compressor rotor for geared turbofan engine. United Technologies Corporation, Carlson Gaskey & Olds PC, May 6, 2014: US08714913 (1 worldwide citation)

A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive turbine rotor that drives the compressor rotor. The compres ...


8
David A Topol, Bruce L Morin: Low noise compressor rotor for geared turbofan engine. United Technologies Corporation, Carlson Gaskey & Olds PC, April 18, 2017: US09624834

A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive turbine rotor that drives the compressor rotor. The compres ...


9
David A Topol, Bruce L Morin, Detlef Korte: Low noise compressor and turbine for geared turbofan engine. UNITED TECHNOLOGIES CORPORATION, MTU AERO ENGINES, Carlson Gaskey & Olds P C, August 15, 2017: US09733266

A gas turbine engine has a fan, a turbine section having a first turbine including a first turbine rotor, a compressor rotor, and a gear reduction configured to effect a reduction in a speed of the fan relative to an input speed from the first turbine rotor. Each of the compressor rotor and the firs ...


10
David A Topol, Bruce L Morin, Detlef Korte: Low noise compressor and turbine for geared turbofan engine. United Technologies Corporation, MTU Aero Engines, Carlson Gaskey & Olds PC, May 16, 2017: US09650965

A gas turbine engine according to an example of the present disclosure includes, among other things, a fan, a turbine section having a fan drive turbine rotor, and a compressor rotor. A gear reduction is configured to effect a reduction in a speed of the fan relative to an input speed from the fan d ...