A turbine nozzle assembly system, comprising: a plurality of nozzle sets (115, 115A-D)), each nozzle set (115, 115A-D) including a plurality of nozzles that collectively form an annulus of a particular nozzle stage (L0-L3) of a turbine, characterised by each nozzle of a respective nozzle set including an airfoil (128, 128A-D) having: an inner endwall mount end, an outer endwall mount end, and a wing portion (130, 130A-B) between the inner endwall mount end and the outer endwall mount end; an inner endwall including a first joint opening (150, 152) configured to receive the inner endwall mount end of the airfoil (128, 128A-D); an outer endwall including a second joint opening (150, 152) configured to receive the outer endwall mount end of the airfoil (128, 128A-D); wherein the inner endwall mount ends amongst the plurality of nozzle sets (115, 115A-D) are identical to each other, wherein the outer endwall mount ends amongst the plurality of nozzle sets (115, 115A-D) are identical to each other, wherein the wing portions (130, 130A-B) of a respective nozzle set (115, 115A-D) of the plurality of nozzle sets (115, 115A-D) have a wing shape that is identical for each airfoil (128, 128A-D) within the respective nozzle set but different than the wing shapes of the wing portions of the other nozzle sets (115, 115A-D) of the plurality of nozzle sets (115, 115A-D), wherein for each nozzle set (115, 115A-D): adjacent nozzles of the plurality of nozzles define a pairwise throat area created by the respective inner endwalls, the respective outer endwalls and the respective wing portions of the adjacent airfoils (128, 128A-B) in the annulus of the particular nozzle stage (L0-L3) of the turbine, and wherein the pairwise throat area of each nozzle set of the plurality of nozzle sets (115, 115A-D) is identical for each pairwise throat area within the respective nozzle set but different than the pairwise throat areas of the other nozzle sets of the plurality of nozzle sets (115, 115A-D). an airfoil (128, 128A-D) having: an inner endwall mount end, an outer endwall mount end, and a wing portion (130, 130A-B) between the inner endwall mount end and the outer endwall mount end; an inner endwall mount end, an outer endwall mount end, and a wing portion (130, 130A-B) between the inner endwall mount end and the outer endwall mount end; an inner endwall including a first joint opening (150, 152) configured to receive the inner endwall mount end of the airfoil (128, 128A-D); an outer endwall including a second joint opening (150, 152) configured to receive the outer endwall mount end of the airfoil (128, 128A-D); wherein the inner endwall mount ends amongst the plurality of nozzle sets (115, 115A-D) are identical to each other, wherein the outer endwall mount ends amongst the plurality of nozzle sets (115, 115A-D) are identical to each other, wherein the wing portions (130, 130A-B) of a respective nozzle set (115, 115A-D) of the plurality of nozzle sets (115, 115A-D) have a wing shape that is identical for each airfoil (128, 128A-D) within the respective nozzle set but different than the wing shapes of the wing portions of the other nozzle sets (115, 115A-D) of the plurality of nozzle sets (115, 115A-D), wherein for each nozzle set (115, 115A-D): adjacent nozzles of the plurality of nozzles define a pairwise throat area created by the respective inner endwalls, the respective outer endwalls and the respective wing portions of the adjacent airfoils (128, 128A-B) in the annulus of the particular nozzle stage (L0-L3) of the turbine, and wherein the pairwise throat area of each nozzle set of the plurality of nozzle sets (115, 115A-D) is identical for each pairwise throat area within the respective nozzle set but different than the pairwise throat areas of the other nozzle sets of the plurality of nozzle sets (115, 115A-D).