Abstract: An expansion joint seal between a gas turbine exhaust duct and an axially adjacent exhaust ductwork comprising plural layers of axially adjacent layers of flexible seal plates, each layer comprising a plurality of arcuate segments which together form a 360.degree. annulus; and further wherein the plural layers of flexible seal plates are secured at one end to the gas turbine exhaust duct, with opposite ends of the seal plates slidably engaged with at least one surface of the exhaust ductwork.

Abstract: The high pressure inlet bleed heat system includes a plurality of tubes which receive heated compressed air from the compressor extraction discharge manifold. The tubes extend into the inlet duct of the compressor, are uniformly spaced one from the other and have a uniform distribution of laterally opening apertures along their lengths in registration with the apertures of next laterally adjacent tubes. The tubes are located downstream of the silencer baffles. By providing choked flow through the apertures and lateral registration of the apertures of adjacent tubes, complete mixing of the heated air with the inlet air vortices behind the silencer baffles is achieved, affording a uniform temperature distribution across the inlet duct with minimum pressure loss. The tubes are constructed to accommodate thermal expansion of the manifold receiving compressor discharge air, the manifold also being supported to accommodate thermal expansion and contraction.