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 (F0) 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 (F1) received in the intake conduit into a particle flow (F2) and an air flow (F3), and an inlet conduit and a bypass conduit located on respective opposite sides of the splitter , the inlet conduit receiving the air flow (F3), 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 (F2), the bypass conduit in fluid flow communication with an environment (E) 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 (F0) 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 (F1) received in the intake conduit into a particle flow (F2) and an air flow (F3), and an inlet conduit and a bypass conduit located on respective opposite sides of the splitter , the inlet conduit receiving the air flow (F3), 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 (F2), the bypass conduit in fluid flow communication with an environment (E) 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 (F1) received in the intake conduit into a particle flow (F2) and an air flow (F3), and an inlet conduit and a bypass conduit located on respective opposite sides of the splitter , the inlet conduit receiving the air flow (F3), 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 (F2), the bypass conduit in fluid flow communication with an environment (E) 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 . <EOS>