can be supplied to the higher pressure area on the radially outer side of the seal application_number US 201314064918 A description fig1 is a cross sectional side view of a conventional gas turbine engine 10 taken along a longitudinal axis 12 i e the axis of rotation of the turbine rotor with reference also to the enlarged detail in fig2 it will be appreciated that air enters the gas turbine engine 10 through the air intake section 14 of a compressor 16 the compressed air exiting the compressor 16 is directed to the combustors 18 one shown to mix with fuel which combusts to generate hot combustion gases multiple combustors 18 may be annularly disposed within the turbine combustor section 20 and each combustor 18 may include a transition piece 22 that directs the hot combustion gases from the respective combustor 18 to the gas turbine section 24 in other words each transition piece 22 defines a hot gas path from its respective combustor 18 to the turbine section 24 the illustrated exemplary gas turbine section 24 includes three separate stages 26 each stage 26 includes a set or row of buckets 28 coupled to a respective rotor wheel 30 that is rotatably attached to the turbine rotor or shaft represented by the axis of rotation 12 between each wheel 30 is a set of nozzles 40 incorporating a circumferential row of stationary vanes.