Abstract: Disclosed are methods and systems for performing uncertainty calculations. For example, a numeric value and an error range associated with the numeric value are converted by a processor into a trans-imaginary input dual which is a hybrid of numeric and geometric information having real and complex numbers. A dual calculation is performed using the trans-imaginary input dual to produce a trans-imaginary output dual, and the processor then converts the trans-imaginary output dual to a real number output numeric value that includes both a real number and real number error range or uncertainty associated with that real number.

Abstract: Disclosed are methods and systems for performing uncertainty calculations. For example, a numeric value and an error range associated with the numeric value are converted by a processor into a trans-imaginary input dual which is a hybrid of numeric and geometric information having real and complex numbers. A dual calculation is performed using the trans-imaginary input dual to produce a trans-imaginary output dual, and the processor then converts the trans-imaginary output dual to a real number output numeric value that includes both a real number and real number error range or uncertainty associated with that real number.

Abstract: Disclosed are methods and systems for performing uncertainty calculations. For example, a first numeric value and an error range associated with the first numeric value is converted by a processor into a dual number, which is then converted into an input chordal, where the input chordal is both a numeric and a geometric form of the dual number. A chordal calculation is performed using the input chordal to create an output chordal, and the processor then converts the output chordal to an output numeric value that comprises both a number and an error range associated with that number.

Abstract: A cooling circuit is provided disposed between a first wall portion and a second wall portion of a wall for use in a gas turbine engine, one or more inlet apertures, and one or more exit apertures. The inlet aperture(s) provides a cooling airflow path into the cooling circuit and the exit aperture(s) provides a cooling airflow path out of the cooling circuit. The cooling circuit includes a plurality of first pedestals extending between the first wall portion and the second wall portion. The first pedestals are arranged in one or more rows.

Abstract: A cooling circuit is provided disposed between a first wall portion and a second wall portion of a wall for use in a gas turbine engine, one or more inlet apertures, and one or more exit apertures. The inlet aperture(s) provides a cooling airflow path into the cooling circuit and the exit aperture(s) provides a cooling airflow path out of the cooling circuit. The cooling circuit includes a plurality of first pedestals extending between the first wall portion and the second wall portion. The first pedestals are arranged in one or more rows.

Abstract: According to the present invention, a cooling circuit is provided disposed between a first wall portion and a second wall portion of a wall for use in a gas turbine engine, one or more inlet apertures, and one or more exit apertures. The inlet aperture(s) provides a cooling airflow path into the cooling circuit and the exit aperture(s) provides a cooling airflow path out of the cooling circuit. The cooling circuit includes a plurality of first pedestals extending between the first wall portion and the second wall portion. The first pedestals are arranged in one or more rows.

Abstract: According to the present invention, a method and an apparatus for cooling a wall within a gas turbine engine is provided. The apparatus includes and the method provides for a cooling circuit disposed within a wall having utility within a gas turbine engine. The cooling circuit includes a forward end, an aft end. The pedestals extend between first and second portions of the wall. The characteristics and array of the pedestals within the cooling circuit are chosen to provide a heat transfer cooling profile within the cooling circuit that substantially offsets the profile of the thermal load applied to the wall portion containing the cooling circuit. At least one inlet aperture provides a cooling airflow path into the forward portion of the cooling circuit from the cavity. A plurality of exit apertures provide a cooling airflow path out of the aft portion of the cooling circuit and into the core gas path outside the wall.

Abstract: A coolable airfoil is disclosed which includes an internal cavity, an external wall, a plurality of first apertures, and a plurality of second apertures. The external wall includes a suction-side portion and a pressure-side portion. The external wall portions extend chordwise between a leading edge and a trailing edge, and spanwise between an inner radial surface and an outer radial surface. The mean camber line of the airfoil passes through the leading edge and the trailing edge along a path equidistant between the outer surfaces of the pressure-side and suction-side walls. The first apertures, which are disposed in the external wall adjacent the trailing edge, extend a distance within the suction-side wall portion and exit the external wall through the pressure-side wall portion. The second apertures extend through the pressure-side wall portion and exit the pressure-side wall portion upstream of and in close proximity to the first apertures.

Abstract: A coolable airfoil is provided which includes an internal cavity, an external wall, a plurality of first cooling apertures, and a plurality of second cooling apertures. The external wall includes a suction side portion and a pressure side portion. The wall portions extend chordwise between a leading edge and a trailing edge and spanwise between an inner radial surface and an outer radial surface. The first cooling apertures are disposed in the external wall adjacent the trailing edge, exiting the airfoil through the pressure side portion. The second cooling apertures are disposed in the external wall adjacent the trailing edge, exiting the airfoil through the suction side portion.