A turbine engine airfoil comprising: a first wall ; a second wall ; a first dividing wall spaced radially between inner and outer platforms of the airfoil and spanning between and engaging the first and second walls ; a second dividing wall spaced between the first and second walls and spanning radially between and the engaging the inner and outer platforms of the airfoil , the second dividing wall isolating a first chamber portion from a second chamber portion ; a first baffle spaced between the first and second walls and located in the first chamber portion ; and a second baffle spaced between the first and second walls and located in the second chamber portion , wherein the first wall and the baffles define a respective upstream cooling path therebetween having an upstream end portion and a downstream end portion , the second wall and the baffles define a downstream cooling path therebetween, the baffles each have a first side facing the respective upstream cooling path that at least in-part defines a bleed aperture at the downstream end portion and an opposite second side defining in-part a boundary of the respective downstream cooling path with at least one hole communicating through the second side , no additional apertures are defined in the side at the upstream end portion , film holes in the second wall and apertures in a trailing edge of the airfoil are configured to receive cooling air from the downstream cooling path of the first chamber portion , and further film holes in the second wall and film holes in a leading edge of the airfoil are configured to receive cooling air from the downstream cooling path of the second chamber portion . a first wall ; a second wall ; a first dividing wall spaced radially between inner and outer platforms of the airfoil and spanning between and engaging the first and second walls ; a second dividing wall spaced between the first and second walls and spanning radially between and the engaging the inner and outer platforms of the airfoil , the second dividing wall isolating a first chamber portion from a second chamber portion ; a first baffle spaced between the first and second walls and located in the first chamber portion ; and a second baffle spaced between the first and second walls and located in the second chamber portion , wherein the first wall and the baffles define a respective upstream cooling path therebetween having an upstream end portion and a downstream end portion , the second wall and the baffles define a downstream cooling path therebetween, the baffles each have a first side facing the respective upstream cooling path that at least in-part defines a bleed aperture at the downstream end portion and an opposite second side defining in-part a boundary of the respective downstream cooling path with at least one hole communicating through the second side , no additional apertures are defined in the side at the upstream end portion , film holes in the second wall and apertures in a trailing edge of the airfoil are configured to receive cooling air from the downstream cooling path of the first chamber portion , and further film holes in the second wall and film holes in a leading edge of the airfoil are configured to receive cooling air from the downstream cooling path of the second chamber portion . <EOS>