Ice-interference features for aircraft
AssigneeGeneral Electric Company
InventorsCharles D. Califf, Christopher E. LaMaster
Life of this patent
Estimating the term…
Abstract
An example booster splitter includes an inner cylindrical structure; an outer cylindrical structure concentric with the inner cylindrical structure; an annular lip having an arc extending between the inner cylindrical structure and the outer cylindrical structure; a first protrusion at a first circumferential position on the annular lip, the first protrusion protruding axially from the annular lip and extending from the outer cylindrical structure to the inner cylindrical structure along the arc of the annular lip; and a second protrusion at a second circumferential position on the annular lip.
Claims19
A booster splitter for an engine, the booster splitter comprising:
- an inner cylindrical structure;
- an outer cylindrical structure concentric with the inner cylindrical structure;
- an annular lip having an arc extending between the inner cylindrical structure and the outer cylindrical structure;
- a first protrusion at a first circumferential position on the annular lip, the first protrusion protruding axially from the annular lip and extending from the outer cylindrical structure to the inner cylindrical structure along the arc of the annular lip, the first protrusion including:
- a first end defining a first length coupled to the annular lip, and a second end opposite the first end defining a second length where the second length is larger than the first length, the second end protruding axially from the annular lip a protruding depth;
- and
- a first concave fillet surface and a second concave fillet surface each extending between the first end and the second end, the first concave fillet surface and the second concave fillet surface facing in opposite circumferential directions;
- and
- a second protrusion at a second circumferential position on the annular lip.
A booster splitter for an engine, the booster splitter comprising:
- an annular lip;
- a first protrusion at a first position on the annular lip, the first protrusion extending axially from the annular lip, the first protrusion including:
- a first end defining a first length coupled to the annular lip, the first end defining a second length where the second length is larger than the first length, the second end protruding axially from the annular lip a protruding depth;
- and
- a first concave fillet surface and a second concave fillet surface each extending between the first end and the second end, the first concave fillet surface and the second concave fillet surface facing in opposite circumferential directions, and the first and second concave fillet surfaces based on a radius of curvature;
- and
- a second protrusion at a second position on the annular lip including a third concave fillet surface and a fourth concave fillet surface, the third and fourth concave fillet surfaces based on the radius of curvature.
An aircraft engine comprising:
- a booster splitter;
- an annular lip on the booster splitter;
- a first ice-interference structure extending axially from the annular lip along an arc of the annular lip between an outer cylindrical structure and an inner cylindrical structure of the booster splitter, the first ice-interference structure including
- a first end defining a first length coupled to the annular lip, and a second end opposite the first end defining a second length where the second length is larger than the first length, the second end protruding axially from the annular lip a protruding depth;
- and
- a first concave fillet surface and a second concave fillet surface each extending between the first end and the second end, the first concave fillet surface and the second concave fillet surface facing in opposite circumferential directions;
- and
- a second ice-interference structure extending from the annular lip.
Dependencies are inferred from the claim text.