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US 6,546,731 B2Granted
Combustion chamber for a gas turbine engine
AssigneeABB Alstom Power UK Ltd.
InventorsHisham Salman Alkabie, Robin Thomas David McMillan
Life of this patent
Estimating the term…
Abstract
In a twin wall combustion chamber for a gas turbine engine, the outer wall has impingement holes so that compressed air surrounding the chamber can pass through the holes to impinge on the inner wall, and the inner wall has effusion holes whereby air can effuse into the combustion chamber. The number of effusion holes is greater than the number of impingement holes, the effusion-holes preferably being arranged in groups of seven, comprising six holes equi-spaced around a central seventh hole, each group having an impingement hole in a fixed positional relationship to the central hole, preferably downstream of it.
Claims17
A combustion chamber for a gas turbine engine, the combustion chamber comprising:
- a) upstream and downstream ends relative to a direction of combustion gas flow therethrough,
- b) an inner wall,
- c) an outer wall spaced apart from the inner wall such that confronting surfaces of the outer and inner walls do not abut each other, thereby to define a cavity between the walls,
- d) the outer wall having a plurality of impingement cooling holes therethrough connecting with the cavity, whereby, during operation of the engine, compressed air surrounding the chamber passes through the impingement holes to impinge on the inner wall,
- e) the inner wall having a plurality of effusion holes therethrough, whereby air effuses from the cavity between the inner and outer walls into the combustion chamber, there being a greater number of effusion holes than impingement holes, and
- f) the effusion holes being arranged in groups, each group comprising a plurality of the effusion holes substantially equally spaced apart from each other around a central effusion hole, each group of effusion holes having an impingement hole located in the outer wall such that air passing through the impingement hole impinges on the inner wall at a predetermined position offset relative to the central effusion hole within a boundary defined by the group of effusion holes, said impingement within the boundary being a first contact of the air with the inner wall after the air has passed through the impingement hole.
3 more elements
A gas turbine engine containing at least one combustion chamber, the combustion chamber comprising:
- a) upstream and downstream ends relative to a direction of combustion gas flow therethrough,
- b) an inner wall,
- c) an outer wall spaced apart from the inner wall such that confronting surfaces of the outer and inner walls do not abut each other, thereby to define a cavity between the walls,
- d) the outer wall having a plurality of impingement cooling holes therethrough connecting with the cavity, whereby, during operation of the engine, compressed air surrounding the chamber passes through the impingement holes to impinge on the inner wall,
- e) the inner wall having a plurality of effusion holes therethrough, whereby air effuses from the cavity between the inner and outer walls into the combustion chamber, there being a greater number of effusion holes than impingement holes, and
- f) the effusion holes being arranged in groups, each group comprising a plurality of the effusion holes substantially equally spaced apart from each other around a central effusion hole, each group of effusion holes having an impingement hole located in the outer wall such that air passing through the impingement hole impinges on the inner wall at a predetermined position offset relative to the central effusion hole within a boundary defined by the group of effusion holes, said impingement within the boundary being a first contact of the air with the inner wall after the air has passed through the impingement hole.
3 more elements
A combustion chamber for a gas turbine engine, the combustion chamber comprising:
- a) upstream and downstream ends relative to a direction of combustion gas flow therethrough,
- b) an inner wall,
- c) an outer wall spaced apart from the inner wall thereby to define a cavity between the walls,
- d) the outer wall having a plurality of impingement cooling holes therethrough, whereby, during operation of the engine, compressed air surrounding the chamber passes through the impingement holes to impinge on the inner wall,
- e) the inner wall having a plurality of effusion holes therethrough, whereby air effuses from the cavity between the inner and outer walls into the combustion chamber, there being a greater number of effusion holes than impingement holes, and
- f) the effusion holes being arranged in groups of seven, each group comprising six effusion holes substantially equally spaced apart from each other around a central seventh effusion hole, each group of effusion holes having an impingement hole located in the outer wall such that air passing through the impingement hole impinges on the inner wall at a predetermined position relative to the central effusion hole within a boundary defined by the group of effusion holes.
3 more elements
A combustion chamber for a gas turbine engine, the combustion chamber comprising:
- a) upstream and downstream ends relative to a direction of combustion gas flow therethrough,
- b) an inner wall,
- c) an outer wall spaced apart from the inner wall thereby to define a cavity between the walls,
- d) the outer wall having a plurality of impingement cooling holes therethrough, whereby during operation of the engine, compressed air surrounding the chamber passes through the impingement holes to impinge on the inner wall,
- e) the inner wall having a plurality of effusion holes therethrough, whereby air effuses from the cavity between the inner and outer walls into the combustion chamber, there being a greater number of effusion holes than impingement holes, and
- f) the effusion holes being arranged in groups, each group comprising a plurality of the effusion holes substantially equally spaced apart from each other around a central effusion hole, each group of effusion holes having an impingement hole located in the outer wall such that air passing through the impingement hole impinges on the inner wall at a predetermined position relative to the central effusion hole within a boundary defined by the group of effusion holes, the groups of effusion holes being arranged in rows extending circumferentially of the chamber, the groups in any one row being displaced circumferentially from those in an adjacent row by a distance substantially equal to half a separation between the central holes in adjacent groups in a row, additional effusion holes being provided centrally of each set of six holes defined between two adjacent groups in one
3 more elements
Dependencies are inferred from the claim text.