NACELLE INNER LIP SKIN WITH HEAT TRANSFER AUGMENTATION FEATURES
First Claim
1. A nacelle inlet structure for an aircraft propulsion system, comprising:
- an inlet lip comprising an inner lip skin and an outer lip skin;
a bulkhead configured with the inlet lip to form a cavity axially between a forward end of the inlet lip and the bulkhead and radially between the inner lip skin and the outer lip skin, wherein the cavity extends along a longitudinal centerline within the inlet lip;
a nozzle configured to inject fluid approximately longitudinally into the cavity; and
a plurality of heat transfer augmentation features configured with the inner lip skin and operable to interact with the fluid within the cavity in order to promote heat transfer between the inner lip skin and the fluid within the cavity.
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Accused Products
Abstract
A nacelle inlet structure is provided for an aircraft propulsion system. This inlet structure includes an inlet lip, a bulkhead, a nozzle and a plurality of heat transfer augmentation features. The inlet lip includes an inner lip skin and an outer lip skin. The bulkhead is configured with the inlet lip to form a cavity axially between a forward end of the inlet lip and the bulkhead and radially between the inner lip skin and the outer lip skin. The annular cavity extends along a curvilinear centerline within the inlet lip. The nozzle is configured to inject fluid approximately tangentially into the annular cavity. The heat transfer augmentation features are configured with the inner lip skin and operable to interact with the fluid flow within the cavity in order to promote heat transfer between the inner lip skin and the fluid within the cavity.
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Citations
20 Claims
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1. A nacelle inlet structure for an aircraft propulsion system, comprising:
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an inlet lip comprising an inner lip skin and an outer lip skin; a bulkhead configured with the inlet lip to form a cavity axially between a forward end of the inlet lip and the bulkhead and radially between the inner lip skin and the outer lip skin, wherein the cavity extends along a longitudinal centerline within the inlet lip; a nozzle configured to inject fluid approximately longitudinally into the cavity; and a plurality of heat transfer augmentation features configured with the inner lip skin and operable to interact with the fluid within the cavity in order to promote heat transfer between the inner lip skin and the fluid within the cavity. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14)
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15. A nacelle inlet structure for an aircraft propulsion system, comprising:
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an inlet lip comprising an inner lip skin and an outer lip skin; and a bulkhead configured with the inlet lip to form an annular cavity axially between a forward end of the inlet lip and the bulkhead and radially between an outer side of the inner lip skin and an inner side of the outer lip skin, wherein the cavity extends along an annular curvilinear centerline within the inlet lip; wherein at least a portion of the outer side of the inner lip skin that forms the cavity comprises a relatively rough textured surface, and substantially all of the inner side of the outer lip skin that forms the cavity consists essentially of a substantially smooth surface. - View Dependent Claims (16, 17, 18)
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19. A nacelle inlet structure for an aircraft propulsion system, comprising:
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an inlet lip comprising an inner lip skin and an outer lip skin; a bulkhead configured with the inlet lip to form an annular cavity axially between a forward end of the inlet lip and the bulkhead and radially between an outer side of the inner lip skin and an inner side of the outer lip skin, wherein the annular cavity extends along a curvilinear centerline within the inlet lip; and a plurality of parallel ribs at the outer side of the inner lip skin. - View Dependent Claims (20)
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Specification