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US 7,093,439 B2Granted
Heat shield panels for use in a combustor for a gas turbine engine
AssigneeUnited Technologies Corporation
InventorsMonica Pacheco-Tougas, Joseph D. Coughlan, III, James B. Hoke, Alan J. Goetschius
Life of this patent
Estimating the term…
Abstract
The present invention relates to heat shield panels or liners to be used in combustors for gas turbine engines. The heat shield panels each comprise a hot side and a cold side and at least one isolated cooling chamber on the cold side. Each cooling chamber has a plurality of cooling film holes for allowing a coolant, such as air, to flow from the cold side to the hot side. A combustor having an arrangement of heat shield panels or liners is also described.
Claims54
A heat shield panel for use in a combustor for a gas turbine engine, comprising:
- a hot side and a cold side;
- said cold side having a plurality of cooling chambers;
- each said cooling chamber having a plurality of film holes for allowing a coolant to flow from said cold side to said hot side;
- said cold side having a front boundary wall and a rear boundary wall;
- a plurality of inner rails extending between said front boundary wall and said rear boundary wall;
- at least one of said cooling chambers being formed by said front boundary wall, said rear boundary wall, and said inner rails;
- and
- said front boundary wall having a means for metering air flow over a leading edge of said panel and said metering means being formed by a plurality of rows of spaced apart pins.
5 more elements
A heat shield panel for use in a combustor for a gas turbine engine, comprising:
- a hot side and a cold side;
- said cold side having a plurality of cooling chambers;
- each said cooling chamber having a plurality of film holes for allowing a coolant to flow from said cold side to said hot side;
- said cold side having a front boundary wall and a rear boundary wall;
- a plurality of inner rails extending between said front boundary wall and said rear boundary wall;
- at least one of said cooling chambers being formed by said front boundary wall, said rear boundary wall, and said inner rails;
- and
- said rear boundary wall being formed by a means for metering air flow over an edge of said panel and said metering means comprising a plurality of first pin arrays and a plurality of second pin arrays.
5 more elements
A heat shield panel for use in a combustor for a gas turbine engine, comprising:
- a hot side and a cold side;
- said cold side having a plurality of cooling chambers;
- each said cooling chamber having a plurality of film holes for allowing a coolant to flow from said cold side to said hot side;
- a plurality of major dilution holes and a plurality of minor dilution holes positioned adjacent a trailing edge of said panel;
- and
- said panel having axially extending rails and attachment posts and wherein said cooling holes have an orientation on one side of each said rail and each said attachment post which is locally reversed so that said coolant flows over said rail and said attachment post.
3 more elements
A heat shield panel for use in a combustor for a gas turbine engine, comprising:
- a hot side and a cold side;
- said cold side having a plurality of cooling chambers;
- each said cooling chamber having a plurality of film holes extending from said cold side to said hot side for allowing a coolant to flow from said cold side to said hot side;
- a plurality of major dilution holes and a plurality of minor dilution holes positioned adjacent a trailing edge of the panel;
- and
- wherein the density of said cooling holes in the vicinity of said major dilution holes is increased.
3 more elements
A heat shield panel for use in a combustor for a gas turbine engine, comprising:
- a hot side and a cold side;
- said cold side having a plurality of cooling chambers;
- each said cooling chamber having a plurality of film holes for allowing a coolant to flow from said cold side to said hot side;
- each of said cooling chambers having an axially extending zigzag line located circumferentially midway between wall portions forming sides of said cooling chamber;
- said cooling holes on a first side of said zigzag line all being obliquely oriented so that the coolant issues from said cooling holes with a first circumferential direction component toward a first one of said side wall portions;
- and
- said cooling holes on a second side of said zigzag line all being obliquely oriented so that the coolant issues from said cooling holes with a second circumferential direction component toward a second one of said side wall portions.
4 more elements
A combustor for a gas turbine engine comprising:
- an outer support shell and an inner support shell;
- said inner and outer support shells forming a combustion chamber;
- an array of forward heat shield panels attached to said inner and outer support shells;
- an array of rear heat shield panels attached to said inner and outer support shells;
- said forward heat shield panels each having a plurality of dilution holes through which air passes into said combustion chamber;
- said rear heat shield panels each having a plurality of rails;
- and
- said rails in each said rear heat shield panel being circumferentially offset with respect to radially opposed ones of said dilution holes to mitigate any loss of cooling effectiveness.
5 more elements
A heat shield panel for use in a combustor for a gas turbine engine, comprising:
- a hot side and a cold side;
- a plurality of cooling holes extending from said hot side and said cold side;
- a plurality of inner rails on said cold side of said panel;
- a first set of said cooling holes circumferentially proximate said rails comprising oblique cooling holes;
- and
- remaining ones of said cooling holes being oriented at zero degrees or ninety degrees with respect to a mean combustor airflow direction.
3 more elements
A heat shield panel for use in a combustor for a gas turbine engine, comprising:
- a cold side and a hot side;
- a plurality of film cooling holes extending from said cold side to said hot side;
- an end wall and a pair of side walls extending from said cold side and mating with a support shell of said combustor, said end wall and said pair of side walls directing coolant air through said plurality of film cooling holes so as to form a film of coolant air over said hot side;
- and
- means near an edge of said panel for metering flow of said coolant air over said edge of said panel and for exhausting said coolant air to flow over said panel edge.
2 more elements
A heat shield panel for use in a combustor for a gas turbine engine comprising:
- at least one chamber on a cold side of said heat shield panel;
- a first set of cooling holes passing through said heat shield panel;
- a second set of cooling holes passing through said heat shield panel, said second set of cooling holes having a different angular orientation than said first set of cooling holes;
- and
- said at least one chamber is bounded by a rail and said first set of cooling holes are oriented to blow cooling air onto said rail.
2 more elements
A heat shield panel for use in a combustor for a gas turbine engine comprising:
- at least one chamber on a cold side of said heat shield panel;
- a first set of cooling holes passing through a wall of said heat shield panel;
- a second set of cooling holes passing through said wall of said heat shield panel, said second set of cooling holes having a different angular orientation than said first set of cooling holes;
- and
- further comprising at least one attachment post and said first set of cooling holes being oriented to blow cooling air onto said at least one attachment post.
2 more elements
A heat shield panel for use in a combustor for a gas turbine engine comprising:
- at least one chamber on a cold side of said heat shield panel;
- a first set of cooling holes passing through said heat shield panel;
- a second set of cooling holes passing through said heat shield panel, said second set of cooling holes having a different angular orientation than said first set of cooling holes;
- and
- at least one dilution hole and said first set of cooling holes being oriented to blow cooling air towards said dilution hole.
2 more elements
A heat shield for use in a combustor for a gas turbine engine comprising:
- at least one chamber on a cold side of said heat shield panel;
- a first set of cooling holes passing through said heat shield panel;
- a second set of cooling holes passing through said heat shield panel, said second set of cooling holes having a different angular orientation than said first set of cooling holes;
- at least one dilution hole and said first set of cooling holes being oriented to blow cooling air towards said dilution hole;
- and
- wherein said panel has an end wall and said first set of cooling holes are positioned adjacent said end wall and are oriented at 90 degrees with respect to a mean combustor air flow direction.
3 more elements
Dependencies are inferred from the claim text.