A gas turbine engine, comprising: a compressor section; a turbine section downstream of the compressor section, the turbine section having a rotor rotatable about a central axis; and an inertial particle separator (30; 130) located upstream of the turbine section and downstream of the compressor section relative to a cooling air flow from the compressor section, the inertial particle separator (30; 130) having: an intake conduit in fluid flow communication with the compressor section, the intake conduit defining an elbow, a splitter, a leading edge of the splitter located downstream of the elbow, the splitter located to divide a flow received in the intake conduit into a particle flow and an air flow, and an inlet conduit and a bypass conduit located on respective opposite sides of the splitter, the inlet conduit receiving the air flow, the inlet conduit in fluid flow communication with a cavity (28a; 128a) containing the rotor for cooling the rotor of the turbine section, the bypass conduit receiving the particle flow, the bypass conduit in fluid flow communication with an environment outside the gas turbine engine while bypassing the cavity (28a; 128a) containing the rotor, wherein the turbine section includes stator vanes located upstream of the rotor, the stator vanes secured to a structural member, characterised in that the intake conduit extends in an aperture defined through the structural member. a compressor section; a turbine section downstream of the compressor section, the turbine section having a rotor rotatable about a central axis; and an inertial particle separator (30; 130) located upstream of the turbine section and downstream of the compressor section relative to a cooling air flow from the compressor section, the inertial particle separator (30; 130) having: an intake conduit in fluid flow communication with the compressor section, the intake conduit defining an elbow, a splitter, a leading edge of the splitter located downstream of the elbow, the splitter located to divide a flow received in the intake conduit into a particle flow and an air flow, and an inlet conduit and a bypass conduit located on respective opposite sides of the splitter, the inlet conduit receiving the air flow, the inlet conduit in fluid flow communication with a cavity (28a; 128a) containing the rotor for cooling the rotor of the turbine section, the bypass conduit receiving the particle flow, the bypass conduit in fluid flow communication with an environment outside the gas turbine engine while bypassing the cavity (28a; 128a) containing the rotor, wherein the turbine section includes stator vanes located upstream of the rotor, the stator vanes secured to a structural member, characterised in that the intake conduit extends in an aperture defined through the structural member. an intake conduit in fluid flow communication with the compressor section, the intake conduit defining an elbow, a splitter, a leading edge of the splitter located downstream of the elbow, the splitter located to divide a flow received in the intake conduit into a particle flow and an air flow, and an inlet conduit and a bypass conduit located on respective opposite sides of the splitter, the inlet conduit receiving the air flow, the inlet conduit in fluid flow communication with a cavity (28a; 128a) containing the rotor for cooling the rotor of the turbine section, the bypass conduit receiving the particle flow, the bypass conduit in fluid flow communication with an environment outside the gas turbine engine while bypassing the cavity (28a; 128a) containing the rotor, wherein the turbine section includes stator vanes located upstream of the rotor, the stator vanes secured to a structural member, characterised in that the intake conduit extends in an aperture defined through the structural member.