Uniform cooling film replenishment thermal liner assembly
AssigneeUnited Technologies Corporation
InventorsPaul A. Smith, Jr., George J. Kramer
Life of this patent
Estimating the term…
Abstract
A gas turbine engine liner assembly is disclosed having uniformly spaced rows of cooling orifices oriented perpendicular to the combustion gas flow of the engine. The orifices within each row are spaced equidistant from adjacent orifices within the same row, thereby providing a uniform, uninterrupted pattern of cooling orifices over the hot side of the liner. The liner is secured to a component of the gas turbine engine by a plurality of fasteners which are secured to the liner without affecting the uniform pattern of the cooling orifices.
Claims11
A method of making a fluid cooled liner assembly for a gas turbine engine comprising:
- providing a linear including an outer sheet bonded to an inner sheet, the outer sheet having a plurality of rows of cooling orifices uniformly spaced across a first face of the outer sheet, the cooling orifices within each row uniformly spaced from adjacent cooling orifices in the same row, a plurality of dimples in the inner sheet, each dimple having a supply hole therein for introducing cooling fluid into the dimple, each dimple corresponding to one of the cooling orifices and aligned therewith;
- welding a plurality of liner fasteners to the inner sheet, each fastener including a shaft having a head located at one end and a threaded end opposite the head, each head welded to the inner sheet in spaced relation to the adjacent dimples;
- mounting an impingement sheet on the fasteners in spaced relation to the inner sheet;
- and
- securing an attachment strap to each of the fasteners for attaching the liner to a component of the gas turbine engine.
A fluid cooled liner assembly for a gas turbine engine for protecting a component of said engine from combustion gas of said engine, said liner assembly comprising:
- a liner including an outer sheet bonded to an inner sheet, the outer sheet having a plurality of rows of cooling orifices uniformly spaced across a first face of the outer sheet, the cooling orifices within each row spaced equidistant from adjacent cooling orifices in the same row,
- a plurality of dimples in the inner sheet, each dimple extending away from the outer sheet and having a supply hole therein for introducing cooling fluid into the dimple, each dimple corresponding to one of the cooling orifices and aligned therewith;
- a plurality of liner fasteners fixedly secured to the inner sheet in spaced relation to the adjacent dimples, each fastener including a shaft having a head located at one end and an end opposite the head, a integral flange formed into the shaft, said flange located between the head and the end opposite the head, and securing means secured to the end opposite the head;
- an impingement sheet secured to each of said fasteners by one of said nuts, said impingement sheet in spaced relation to the inner sheet defining a plenum therebetween, said impingement sheet having a plurality of impingement holes therein for supplying cooling fluid to said plenum;
- and
- attachment means for attaching the liner to a component of the gas turbine engine, said attachment means secured to said fasteners by said nuts.
Dependencies are inferred from the claim text.