Abstract: A method of operating an exhaust nozzle assembly includes translating a translatable structure between a plurality of operational positions to open and close a flow diverting port extending in an exhaust duct. The longitudinal position of a throat constriction varies with translation of the translatable structure. Additionally, the cross-sectional area of the exhaust duct at the throat constriction may vary with translation of the translatable structure. An exemplary exhaust nozzle is operable in-flight for providing at least partial reverse thrust to at least partly control the velocity of an aircraft. An exemplary exhaust nozzle is operable on the ground to spoil ground idle thrust.

Abstract: Apparatus including an exhaust nozzle assembly having a translatable structure operable to open and close a flow diverting port in an exhaust duct. The translatable structure includes a forward region partly defining a converging nozzle region. The translatable structure includes a rearward region partly defining a diverging nozzle region. The forward region and the rearward region join at an inner edge that partly defines a throat constriction. The translatable structure is translatable between a plurality of operational positions each associated with a longitudinal position of the throat constriction. In a first operational position, the flow diverting port is fully closed. In a second operational position, the flow diverting port is fully opened. In a first intermediate operational position, the flow diverting port is fully closed. In a second intermediate operational position, the flow diverting port is at least partly opened.

Abstract: A method of operating an exhaust nozzle assembly includes translating a translatable structure between a plurality of operational positions to open and close a flow diverting port extending in an exhaust duct. The longitudinal position of a throat constriction varies with translation of the translatable structure. Additionally, the cross-sectional area of the exhaust duct at the throat constriction may vary with translation of the translatable structure. An exemplary exhaust nozzle is operable in-flight for providing at least partial reverse thrust to at least partly control the velocity of an aircraft. An exemplary exhaust nozzle is operable on the ground to spoil ground idle thrust.

Abstract: Apparatus including an exhaust nozzle assembly having a translatable structure operable to open and close a flow diverting port in an exhaust duct. The translatable structure includes a forward region partly defining a converging nozzle region. The translatable structure includes a rearward region partly defining a diverging nozzle region. The forward region and the rearward region join at an inner edge that partly defines a throat constriction. The translatable structure is translatable between a plurality of operational positions each associated with a longitudinal position of the throat constriction. In a first operational position, the flow diverting port is fully closed. In a second operational position, the flow diverting port is fully opened. In a first intermediate operational position, the flow diverting port is fully closed. In a second intermediate operational position, the flow diverting port is at least partly opened.

Abstract: A method for operating a gas turbine engine assembly for an aircraft that includes a wing, wherein the gas turbine engine includes a core gas turbine engine and a fan coupled to the core gas turbine engine, the gas turbine engine assembly extends upstream from the wing and includes a first cowl and a second cowl that is repositionable with respect to the first cowl. The method includes selectively positioning the second cowl in a first operational position such that airflow is channeled from the gas turbine engine across a surface of the wing to facilitate increasing lift, and selectively positioning the second cowl in a second operational position such that the airflow is channeled from the gas turbine engine to effect reverse thrust.

Abstract: A method for applying design for reliability into design for Six Sigma is described. The method includes establishing an appropriate model for reliability as a function of time; determining a reliability transfer function; calculating defects per opportunity per unit of time; entering said defects per opportunity per unit of time into a calculation of value of sigma; selecting one or more noise factors likely to have an impact on reliability; and performing a closed form analytical solution of said impact on reliability using a Monte Carlo analysis. The noise parameters may include one or more assumptions of the hours of usage per year, temperature of use, material quality, part quality, layout of components, extrinsic stresses, supplier quality, interconnection quality, test coverage, shipping damage, installation errors, errors in instructions, customer misuse or other noise factors beyond the control of the designer.

Abstract: A method of developing a confidence level in reliability or producibility prediction scores that includes generating data for a set of factors, inserting the data into scorecards and dashboards, and calculating an overall Z score and Z confidence range. The scorecards and dashboards are used to calculate the confidence level in reliability scores. Each reliability or producibility factor may be weighted as to its importance to the overall confidence level. Factors included in the method include accuracy of the critical to quality flowdown; completeness of the critical to quality flowdown; percentage of the design analyzed; comprehensiveness of the design analysis; risk assessment analysis; percentage of component. subassembly or product reuse from other projects; percentage of the design complete; verification of the process capability; plant integration; order to remittance process integration; extent of pilot run; and effectiveness of a test plan.