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US 7,007,483 B2Granted
Turbine engine nozzle
AssigneeUnited Technologies Corporation
InventorDonald W. Peters
Life of this patent
Estimating the term…
Abstract
A convergent/divergent nozzle for a gas turbine engine has a throat portion of non-constant radius of curvature varying from an upstream high value to an intermediate low value and then to a downstream high value.
Claims20
An exhaust nozzle for a gas turbine engine comprising:
- an upstream section having an interior surface converging in a downstream direction;
- and
- a downstream section having an interior surface downstream of the interior surface of the upstream section, the downstream section comprising a circumferentially arrayed plurality of flaps, each flap pivotally coupled to the upstream section for articulation through a range of orientations,
- wherein:
- the interior surface of the downstream section along each flap has a central longitudinal radius of curvature that from upstream to downstream has:
- at least a first value along a first portion;
- at least a second value, less than the first value, and between 0.25 inch and 1.0 inch along a second portion;
- and
- at least a third value, less than the first value, and between 5.0 inches and 10.0 inches along a third portion.
6 more elements
A convergent/divergent exhaust nozzle for a gas turbine engine comprising:
- an upstream section having an interior surface converging in a downstream direction;
- and
- a downstream section having an interior surface downstream of the interior surface of the upstream section, the second portion comprising a circumferentially arrayed plurality of flaps, each flap pivotally coupled to the upstream section for articulation through a range of orientations,
- wherein:
- the interior surface of the downstream section along each flap has a central longitudinal radius of curvature that from upstream to downstream has:
- at least a first value along a first portion;
- at least a second value, less than the first value, and between 0.25 inch and 1.0 inch along a second portion;
- and
- at least a third value, less than the first value, and between 8.0 inches and 14.0 inches along a third portion.
6 more elements
An exhaust nozzle for a gas turbine engine comprising:
- an upstream section comprising a plurality of circumferentially arrayed first flaps and having an interior surface converging in a downstream direction;
- and
- a downstream section comprising:
- a plurality of circumferentially arrayed second flaps, each hinged relative to an associated one of the first flaps;
- a downstream outlet;
- and
- an interior surface downstream of the interior surface of the upstream section,
- wherein a longitudinal profile of said downstream section interior surface has:
- a first portion;
- a second portion downstream of the first portion;
- and
- a third portion downstream of the second portion, the second portion having a radius of curvature that is:
- lower than a radius of curvature of the first portion;
- lower than a radius of curvature of the third portion;
- and
- continuously increasing along an axial span.
13 more elements
Dependencies are inferred from the claim text.