A turbine nozzle cartridge assembly (74, 74') adapted to cooperate with a turbine rotor of an associated turbocharger core, comprising: a. a forward nozzle wall, wherein said forward nozzle wall comprises: i. a first surface of revolution surrounding a forward opening in said turbine nozzle cartridge assembly (74, 74'); and ii. a cylindrical lip located at a forward end of said first surface of revolution, wherein said cylindrical lip is configured to fit over a corresponding cylindrical step extending aftwardly from an associated bearing housing of the turbocharger core, said cylindrical lip incorporates a plurality of radial holes, and said plurality of radial holes are configured to cooperate with a corresponding plurality of radial pins extending radially outward from said cylindrical step, so as to provide for maintaining a concentricity of said turbine nozzle cartridge assembly (74, 74') with respect to said bearing housing when said cylindrical lip is thermally expanded with respect to said cylindrical step; b. an aft nozzle wall, wherein said aft nozzle wall comprises a second surface of revolution concentric with said forward nozzle wall and spaced apart aftwardly therefrom; c. a peripheral inlet to said turbine nozzle cartridge assembly (74, 74') located in a resulting gap between radially-peripheral portions of a forward portion of said forward nozzle wall and said aft nozzle wall; d. a plurality of vanes between said forward and aft nozzle walls; e. a turbine rotor shroud portion aftwardly connected to or extending from said aft nozzle wall, wherein a region between said plurality of vanes and said forward and aft nozzle walls provides for fluid communication between said peripheral inlet and said turbine rotor shroud portion, said turbine rotor shroud portion provides for receiving therewithin at least a portion of the turbine rotor of the associated turbocharger core; f. a nozzle exhaust portion aftwardly connected to or extending from said turbine rotor shroud portion; and g. an external sealing surface on an outside of an aft portion of said nozzle exhaust portion, wherein said external sealing surface is configured to cooperate with a corresponding sealing element (104, 104') so as to provide for maintaining a sealed condition therebetween that is substantially unaffected by thermally-induced expansion or contraction of said turbine nozzle cartridge assembly (74, 74') during operation thereof. a. a forward nozzle wall, wherein said forward nozzle wall comprises: i. a first surface of revolution surrounding a forward opening in said turbine nozzle cartridge assembly (74, 74'); and ii. a cylindrical lip located at a forward end of said first surface of revolution, wherein said cylindrical lip is configured to fit over a corresponding cylindrical step extending aftwardly from an associated bearing housing of the turbocharger core, said cylindrical lip incorporates a plurality of radial holes, and said plurality of radial holes are configured to cooperate with a corresponding plurality of radial pins extending radially outward from said cylindrical step, so as to provide for maintaining a concentricity of said turbine nozzle cartridge assembly (74, 74') with respect to said bearing housing when said cylindrical lip is thermally expanded with respect to said cylindrical step; i. a first surface of revolution surrounding a forward opening in said turbine nozzle cartridge assembly (74, 74'); and ii. a cylindrical lip located at a forward end of said first surface of revolution, wherein said cylindrical lip is configured to fit over a corresponding cylindrical step extending aftwardly from an associated bearing housing of the turbocharger core, said cylindrical lip incorporates a plurality of radial holes, and said plurality of radial holes are configured to cooperate with a corresponding plurality of radial pins extending radially outward from said cylindrical step, so as to provide for maintaining a concentricity of said turbine nozzle cartridge assembly (74, 74') with respect to said bearing housing when said cylindrical lip is thermally expanded with respect to said cylindrical step; b. an aft nozzle wall, wherein said aft nozzle wall comprises a second surface of revolution concentric with said forward nozzle wall and spaced apart aftwardly therefrom; c. a peripheral inlet to said turbine nozzle cartridge assembly (74, 74') located in a resulting gap between radially-peripheral portions of a forward portion of said forward nozzle wall and said aft nozzle wall; d. a plurality of vanes between said forward and aft nozzle walls; e. a turbine rotor shroud portion aftwardly connected to or extending from said aft nozzle wall, wherein a region between said plurality of vanes and said forward and aft nozzle walls provides for fluid communication between said peripheral inlet and said turbine rotor shroud portion, said turbine rotor shroud portion provides for receiving therewithin at least a portion of the turbine rotor of the associated turbocharger core; f. a nozzle exhaust portion aftwardly connected to or extending from said turbine rotor shroud portion; and g. an external sealing surface on an outside of an aft portion of said nozzle exhaust portion, wherein said external sealing surface is configured to cooperate with a corresponding sealing element (104, 104') so as to provide for maintaining a sealed condition therebetween that is substantially unaffected by thermally-induced expansion or contraction of said turbine nozzle cartridge assembly (74, 74') during operation thereof.