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 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 of the gas turbine engine, the leading edge angle and the trailing edge angle both being oriented in the same circumferential direction.