A gas turbine engine , comprising: a compressor section ; a diffuser assembly located aft of the compressor section ; and a stator assembly in the compressor section , wherein the stator assembly comprises: an outer diameter, OD, ring coupled adjacent to the diffuser assembly and having a front edge and an aft edge; an exit guide vane coupled to the OD ring ; an inner diameter, ID, ring coupled adjacent to the diffuser assembly radially apart from the OD ring and having a front end and an aft end, wherein the ID ring is coupled to the exit guide vane ; and an aft ring (245; 345) radially outward of the OD ring , wherein the exit guide vane comprises: a body; a leading edge ; and a trailing edge opposite of the leading edge , wherein the exit guide vane has a constant profile along the height, wherein the gas turbine engine further comprises an aft OD seal located between the coupling of the OD ring and the diffuser assembly , the gas turbine engine further comprises a diffuser assembly seal (240; 340) located between the diffuser assembly and the aft ring (245; 345) of the gas turbine engine ; and the leading edge is oriented at a leading edge angle (δ) of 44° to 64° and the trailing edge is oriented at a trailing edge angle (γ) of 1° to 15°, wherein the leading edge angle (δ) and the trailing edge angle (γ) are defined by an angle from an axis parallel to a central longitudinal axis (A) of the gas turbine engine , the leading edge angle and the trailing edge angle both being oriented in the same circumferential direction. a compressor section ; a diffuser assembly located aft of the compressor section ; and a stator assembly in the compressor section , wherein the stator assembly comprises: an outer diameter, OD, ring coupled adjacent to the diffuser assembly and having a front edge and an aft edge; an exit guide vane coupled to the OD ring ; an inner diameter, ID, ring coupled adjacent to the diffuser assembly radially apart from the OD ring and having a front end and an aft end, wherein the ID ring is coupled to the exit guide vane ; and an aft ring (245; 345) radially outward of the OD ring , an outer diameter, OD, ring coupled adjacent to the diffuser assembly and having a front edge and an aft edge; an exit guide vane coupled to the OD ring ; an inner diameter, ID, ring coupled adjacent to the diffuser assembly radially apart from the OD ring and having a front end and an aft end, wherein the ID ring is coupled to the exit guide vane ; and an aft ring (245; 345) radially outward of the OD ring , a body; a leading edge ; and a trailing edge opposite of the leading edge , wherein the exit guide vane has a constant profile along the height, wherein the gas turbine engine further comprises an aft OD seal located between the coupling of the OD ring and the diffuser assembly , the gas turbine engine further comprises a diffuser assembly seal (240; 340) located between the diffuser assembly and the aft ring (245; 345) of the gas turbine engine ; and the leading edge is oriented at a leading edge angle (δ) of 44° to 64° and the trailing edge is oriented at a trailing edge angle (γ) of 1° to 15°, wherein the leading edge angle (δ) and the trailing edge angle (γ) are defined by an angle from an axis parallel to a central longitudinal axis (A) of the gas turbine engine , the leading edge angle and the trailing edge angle both being oriented in the same circumferential direction. <EOS>