Multi-hole film cooled combuster linear with differential cooling
AssigneeGeneral Electric Company
InventorElias H. Lampes
Life of this patent
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Abstract
A gas turbine engine combustor is provided with a single wall sheet metal liner having a generally annular shape, which may be corrugated, and contains at least one differential pattern of multi-hole film cooling holes. The differential pattern of cooling holes comprises patterns of small closely spaced sharply downstream angled film cooling holes disposed along portions of the liner so as to direct different amounts of film cooling air to different areas of the liner to accommodate differential heating along the liner. One embodiment of the invention includes a plurality of superimposed differential cooling hole patterns derived from a base pattern wherein each preferential pattern is formed by skipping patterns of cooling holes in the base pattern.
Claims16
A gas turbine combustion liner having a hot side and cold side, said liner comprising:
- a single wall shell having at least one differential multi-hole film cooling hole pattern comprising a plurality of small, cylindrical, closely spaced, sharply downstream angled film cooling holes, angles from the cold side to the hot side and wherein said differential multi-hole film cooling pattern comprises at least one pattern of blank spaces superimposed on a corresponding base pattern of said multi-hole film cooling holes,
- said differential multi-hole film cooling hole pattern comprises a modification of a first base cooling hole pattern comprising axially adjacent rows of multi-hole film cooling holes circumferentially offset from each other by about half the distance between said multi-hole film cooling holes of one of said rows, and
- a first differential multi-hole film cooling hole pattern comprises a pattern of blank spaces that omits a plurality of circumferentially adjacent cooling holes in a plurality of rows in said first base cooling hole pattern in an axially repetitive pattern.
A gas turbine combustor liner having a hot side and cold side, said liner comprising:
- a single wall shell having a plurality of superimposed differential multi-hole film cooling hole patterns wherein said differential multi-hole film cooling hole pattern are derived from a first base multi-hole film cooling hole pattern comprising a plurality of small closely spaced sharply downstream angled cylindrical film cooling holes,
- wherein said differential multi-hole film cooling pattern comprises at least one pattern of blank spaces superimposed on a corresponding base pattern of said multi-hole film cooling holes,
- wherein a said first base pattern includes axially adjacent rows of multi-base film cooling holes in which the holes of adjacent rows are circumferentially offset from each other by about half the distance between said multi-hole film cooling holes of one of said rows,
- a first differential multi-hole film cooling hole pattern comprising one row of blanked holes in said first base pattern in a first axially repetitive pattern, and
- a second differential multi-hole film cooling hole pattern comprising one row of blanked holes in said first base pattern in a first axially repetitive pattern, and
- a second differential multi-hole film cooling hole pattern comprising a plurality of rows of blanked circumferentially adjacent cooling holes in a plurality of rows of said base pattern in a second axially repetitive pattern.
A gas turbine combustion section as claimed in clam 13 wherein said film cooling holes have a slant angle slanted downstream from the cold surface of said liner to the hot surface of said liner of about twenty degrees.
Dependencies are inferred from the claim text.