The Boeing Company

Andrew James Dorgan

Chad M Winkler

Eric Lee Werner

Mortaza Mani

Andrew Wham Cary

Nicholas J Moffitt

Tail cone apparatus and methods for reducing nozzle surface temperatures of aircraft engines are disclosed. An example apparatus includes a tail cone to be coupled to an aircraft engine. The tail cone includes a central axis, a cone section, and a plurality of fins. The fins are spaced about the central axis and extend outwardly from an outer surface of the cone section.

Tail cone apparatus and methods for reducing nozzle surface temperatures

Methods and apparatus to model thermal mixing for prediction of multi-stream flows are described. An example method includes determining characteristics of a nozzle of an aircraft; estimating momentum diffusion due to turbulence associated with the nozzle based on the determined characteristics; and estimating thermal diffusion due to the turbulence associated with the nozzle based on the estimated momentum diffusion, wherein the estimating of the thermal diffusion due to the turbulence is based on a spatially varying turbulent Prandtl number.

Methods and apparatus to model thermal mixing for prediction of multi-stream flows

A nozzle effective exit area control system is created with a convergent-divergent nozzle with a divergent portion of the nozzle having a wall at a predetermined angle of at least 12&#xb0; from the freestream direction. Disturbance generators are located substantially symmetrically oppositely on the wall to induce flow separation from the wall with the predetermined wall angle inducing flow separation to extend upstream from each disturbance generator substantially to a throat of the nozzle pressurizing the wall and reducing the effective area of the jet flow at the nozzle exit.

Method and apparatus for variable exhaust nozzle exit area

A thrust vectoring system is created with a convergent-divergent nozzle having a total angle no greater than 150 degrees. A divergent portion of the nozzle has a wall at a predetermined angle of at least 12&#xb0; from the freestream direction. A disturbance generator is located on the wall to induce flow separation from the wall with the predetermined wall angle sufficient for the induced flow separation to extend upstream from disturbance generator substantially to a throat of the nozzle pressurizing the wall and creating a net vector angle in jet flow through the nozzle.

Method and apparatus for nozzle thrust vectoring

Concepts and technologies are disclosed herein for modeling propulsion-related interfaces in computational fluid dynamics ('CFD'). According to some embodiments disclosed herein, a model is obtained or developed and propulsion-related interfaces within the model are identified. Flow directions of velocities, temperature, and/or mass are calculated adjacent to the propulsion-related interface and compared. A mass flow rate, a conserved variable state jump, a change in flux across the interface, and/or incoming and outgoing flux values can be calculated for the propulsion-related interface. The calculated values can be returned and embedded in the model. The model is solved and a solution is output.

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Edwardsville, IL, United States of America

Andrew James Dorgan