A turbine engine airfoil comprising: a first wall; a second wall; a first dividing wall spaced radially between inner and outer platforms (56, 58) of the airfoil and spanning between and engaging the first and second walls (60, 62); a second dividing wall spaced between the first and second walls (60, 62) and spanning radially between and the engaging the inner and outer platforms (56, 58) of the airfoil, the second dividing wall isolating a first chamber portion (68A, 68C) from a second chamber portion (68B, 68D); a first baffle (86A, 86C) spaced between the first and second walls (60,62) and located in the first chamber portion (68A, 68C); and a second baffle (86B, 86D) spaced between the first and second walls (60, 62) and located in the second chamber portion (68B, 68D), wherein the first wall and the baffles (86A, 86B, 86C, 86D) define a respective upstream cooling path therebetween having an upstream end portion and a downstream end portion, the second wall and the baffles (86A, 86B, 86C, 86D) define a downstream cooling path therebetween, the baffles (86A, 86B, 86C, 86D) 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 (68A, 68C), 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 (68B, 68D). a first wall; a second wall; a first dividing wall spaced radially between inner and outer platforms (56, 58) of the airfoil and spanning between and engaging the first and second walls (60, 62); a second dividing wall spaced between the first and second walls (60, 62) and spanning radially between and the engaging the inner and outer platforms (56, 58) of the airfoil, the second dividing wall isolating a first chamber portion (68A, 68C) from a second chamber portion (68B, 68D); a first baffle (86A, 86C) spaced between the first and second walls (60,62) and located in the first chamber portion (68A, 68C); and a second baffle (86B, 86D) spaced between the first and second walls (60, 62) and located in the second chamber portion (68B, 68D), wherein the first wall and the baffles (86A, 86B, 86C, 86D) define a respective upstream cooling path therebetween having an upstream end portion and a downstream end portion, the second wall and the baffles (86A, 86B, 86C, 86D) define a downstream cooling path therebetween, the baffles (86A, 86B, 86C, 86D) 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 (68A, 68C), 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 (68B, 68D).