This paper presents experimental investigations of the Heat Transfer Coefficient (HTC) performance of a Micro-Tangential-Jet (MTJ) Film cooling scheme on a gas turbine vane using transient Thermochromic Liquid Crystal (TLC) technique. The MTJ scheme is a micro-shaped scheme designed so that the secondary jet is supplied parallel to the vane surface. In order to supply the jet in a direction parallel to the vane surface, extra material was added on both pressure and suction sides. The film cooling performance of one row of holes on both pressure and suction sides were investigated at a blowing ratio ranging from 0.5 to 1.5 on the pressure side and 0.25 to 0.625 on the suction side, calculated based on the MTJ scheme exit area. The average density ratio during the investigations was 0.93, and the Reynolds number was 1.4E+5, based on the free stream velocity and the main duct hydraulic diameter. The pitch to diameter ratio of the cooling holes is 5 on the pressure side and 6.5 on the suction side. The turbulence intensity during all investigations was 8.5% and was measure two chords upstream the vane leading edge using the PIV technique. The investigations showed that the increase in the HTC ratio due to the presence of the MTJ scheme is very close to that resulting from the presence of normal traditional shaped schemes on the pressure side. Meanwhile, a reduction in the HTC ratio is recorded on the suction side. Such performance is attributed to the small overall height of the scheme which helped keep the resulting turbulence to a minimum. Moreover, the HTC distribution downstream the MTJ scheme is uniform in the lateral directions which helps minimize the thermal stresses. The Net Heat Flux Reduction (NHFR) parameter is used to judge the overall performance of the MTJ scheme. The NHFR represents a combination of the effects of both the cooling effectiveness and the HTC. Great enhancement in the NHFR performance of the MTJ was observed compared to traditional shaped schemes. With the current MTJ scheme design and dimensions and under the previously mentioned Reynolds number and turbulence intensity it was observed that a blowing ratio close to unity, calculated based on the scheme exit area, provides an optimal film cooling performance on both pressure and suction sides.