THROAT AREA CALCULATION FOR A SECTION OF A GAS TURBINE ENGINE
A method of calculating a throat area of a section of a machinery, according to an exemplary aspect of the present disclosure includes, among other things, outlining a boundary of the throat area of the section, selecting a plurality of inspection points along the boundary of the throat area, dividing the throat area into a plurality of sections, calculating an individual area of each of the plurality of sections and summing the individual areas of each of the plurality of sections to calculate the throat area.
1 . A method associated for use with a gas turbine engine, comprising:
calculating a throat area of a vane segment of the gas turbine engine by radially dividing the throat area into a plurality of sections, calculating an individual area associated with each of the plurality of sections, and summing the individual areas to calculate the throat area, the vane segment including a first platform and a second platform and a first airfoil and a second airfoil extending between the first platform and the second platform; and
adjusting a design characteristic of the vane segment based on the calculated throat area.
2 . The method as recited in claim 1 , wherein adjusting the design characteristic of the vane segment includes cutting or trimming a portion of the vane segment.
3 . The method as recited in claim 2 , wherein cutting or trimming the portion of the vane segment includes trimming a trailing edge of at least one of the first airfoil and the second airfoil.
4 . The method as recited in claim 2 , wherein cutting or trimming the portion of the vane segment includes machining the portion to remove material.
5 . The method as recited in claim 2 , wherein cutting or trimming the portion of the vane segment includes grinding the portion to remove material.
6 . The method as recited in claim 2 , wherein cutting or trimming the portion of the vane segment includes electrical discharge machining the portion to remove material.
7 . The method as recited in claim 1 , comprising, prior to radially dividing the throat area, outlining a boundary of the throat area of the vane segment by referencing a CAD model of the vane segment.
8 . The method as recited in claim 7 , comprising selecting a plurality of inspection points along the boundary of the throat area.
9 . The method as recited in claim 8 , comprising measuring a location of each of the plurality of inspection points using a coordinate measuring machine (CMM).
10 . The method as recited in claim 1 , comprising comparing the calculated throat area to a desired throat area and adjusting the design characteristic of the vane segment only if the calculated throat area is outside a manufacturing tolerance related to the desired throat area.
11 . A method associated for use with a gas turbine engine, comprising:
inspecting a vane segment of the gas turbine engine, the vane segment including an end wall contoured flow path, and the vane segment including a first platform and a second platform and a first airfoil and a second airfoil extending between the first platform and the second platform;
outlining a boundary of a throat area of the vane segment by referencing a CAD model of the vane segment;
selecting a plurality of inspection points along the boundary of the throat area, at least a portion of the plurality of inspection points being located along the end wall contoured flow path of the vane segment;
measuring a location of each of the plurality of inspection points on an actual casting of the vane segment using a coordinate measuring machine (CMM);
calculating the throat area of the vane segment, including portions of the throat area encompassing the end wall contoured flow path, by radially dividing the throat area into a plurality of sections, calculating an individual area associated with each of the plurality of sections, and summing the individual areas to calculate the throat area; and
adjusting a design characteristic of the vane segment if the calculated throat area is different than a desired throat area.
12 . The method as recited in claim 11 , wherein the end wall contoured flow path includes a plurality of undulations.
13 . The method as recited in claim 11 , comprising adjusting the throat area calculation based on an error value associated the calculated throat area.
14 . The method as recited in claim 11 , wherein adjusting the design characteristic of the vane segment includes cutting or trimming a trailing edge of either the first airfoil or the second airfoil.
15 . The method as recited in claim 14 , wherein cutting or trimming the trailing edge includes machining or grinding the trailing edge to remove material from the vane segment.