Translating multi-ring inlet for gas turbine engines

Claim 2

An inlet for gas turbine engine with air flow through the inlet controlled by a variable geometry apparatus comprising: a first set of concentric rings positioned across an opening to the inlet, a second set of concentric rings located to translate axially into and out of interjacent position with the first set of concentric rings to present a reduced area for air flow when in interjacent position and to present an enlarged area for air flow when moved out of the interjacent position, means for translating the second set of concentric rings, and the distance between concentric rings in each set increase with the distance from the axis.

Claim 3

An inlet for a gas turbine engine as in claim 1, wherein the outermost ring is spaced at a greater distance from the inner wall of the inleT than the distance between the rings.

Claim 4

An inlet for a gas turbine engine with air flow through the inlet controlled by a variable geometry apparatus comprising: a first set of concentric rings positioned across an opening to the inlet, a second set of concentric rings located to translate axially into and out of interjacent position with the first set of concentric rings to present a reduced area for air flow when in interjacent position and to present an enlarged area for air flow when moved out of the interjacent position, means for translating the second set of concentric rings, the first set of concentric rings is supported at the leading streamwise edges by radially extending struts, and the second set of concentric rings is supported at the trailing streamwise edges by radially extending struts.

Claim 5

An inlet for a gas turbine engine with air flow through the inlet controlled by a variable geometry apparatus comprising: a first set of concentric rings positioned across an opening to the inlet, a second set of concentric rings located to translate axially into and out of interjacent position with the first set of concentric rings to present a reduced area for air flow when in interjacent position and to present an enlarged area for air flow when moved out of the interjacent position, means for translating the second set of concentric rings, the first set of concentric rings is supported at the leading streamwise edges by radially extending struts, and the second set of concentric rings is supported at the trailing streamwise edges by radially extending struts.

Claim 6

An inlet for a gas turbine engine as in claim 3, wherein a peripheral end of each strut supporting the second set of concentric rings is mounted to a movable carriage.

Claim 7

An inlet for a gas turbine engine as in claim 4, wherein the sets of concentric rings are shaped aerodynamically.

Claim 8

An inlet for a gas turbine engine as in claim 4, wherein the distance between concentric rings in a set increases from the axis outward, and the distance between the outward ring and an innter inlet wall is greater than the distance between the furtherest apart rings.

Claim 9

An inlet for a gas turbine engine with air flow through the inlet controlled by a variable geometry apparatus comprising: a first set of struts extending radially across an inlet throat; a first set of concentric rings mounted to a downstream side of the first set of struts; a second set of struts extending radially across the inlet movably mounted for reciprocal axial movement; a second set of concentric rings mounted to an upstream side of the second set of struts, said concentric rings located to move into interjacent position with the first set of concentric rings when the second set of struts translate upstream and out of interjacent position when said struts translate downstream, and means for imparting movement to the second set of struts with concentric rings.

Claim 10

An inlet for a gas turbine engine with air flow through the inlet controlled by a variable geometry apparatus comprising: a first set of struts extending radially across an inlet throat; a first set of concentric rings mounted to a downstream side of the first set of struts; a second set of struts extending radially across the inlet movably mounted for reciprocal axial movement; a second set of concentric rings mounted to an upstream side of the second set of struts, said concentric rings located to move into interjacent position with the first set of concentric rings when the second set of struts translate upstream and out of interjacent position when said struts translate downstream, and means for imparting movement to the second set of struts with concentric rings.

Claim 11

An inlet for a gas turbine engine as in claim 7, wherein the concentric rings are aerodynamically shaped.

Claim 12

An inlet for a gas turbine engine as in claim 7, wherein the means for imparting movement to the second set of struts include a carriage attached to a peripheral end of each strut for movement along a track mounted inside the structure of the inlet.

Claim 13

An inlet for a gas turbine engine as in claim 9, wherein the distance between the concentric rings in each set increase from the axis outward and the distance between the outermost ring and the inner wall of the inlet is greater than the distance between the furtherest apart rings.

Claim 14

An inlet for a gas turbine engine with air flow through the inlet controlled by a variable geometry apparatus comprising: an inlet throat, a diffuser area extending downstream from the throat and having an increasing inside cross sectional area, a set of concentric rings extending across the inlet, and means for translating the set of concentric rings between a piston athwart the throat and a position athwart the diffuser area to vary the area for air flow.

Claim 15

An inlet for a gas turbine engine with air flow through the inlet controlled by a variable geometry apparatus comprising: an inlet throat, a diffuser area extending downstream from the throat and having an increasing inside cross sectional area, a set of concentric rings extending across the inlet, and means for translating the set of concentric rings between a piston athwart the throat and a position athwart the diffuser area to vary the area for air flow.

Claim 16

An inlet for a gas turbine engine as in claim 11, wherein the distance between concentric rings increase from an axis outward,

Claim 17

An inlet for a gas turbine engine as in claim 11, wherein the means for translating the concentric rings include a set of radially extending struts to which the rings are mounted, a carriage movable in a track located in the inlet structure, said carriage supporting the peripheral ends of the struts.

Claim 18

An inlet for a gas turbine engine as in claim 13, wherein the distance between concentric rings increase from an axis outward.