Methods and apparatus for passive thrust vectoring and plume deflection
US-2015113946-A1 · Apr 30, 2015 · US
Convergent-divergent nozzle for a turbine engine
US9683516B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9683516-B2 |
| Application number | US-201214363508-A |
| Country | US |
| Kind code | B2 |
| Filing date | Dec 4, 2012 |
| Priority date | Dec 7, 2011 |
| Publication date | Jun 20, 2017 |
| Grant date | Jun 20, 2017 |
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Abstract
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A turbine engine convergent-divergent nozzle including an annular central element and an annular cap arranged coaxially around the central element to co-operate with the central element to define an annular flow channel for a gas stream from the engine. Between a throat section and an ejection section of the nozzle, the central element and the cap present respective internal profiles in longitudinal section that are modeled by curves having respective radii of curvature that are identical in absolute value.
First claim
Opening claim text (preview).
The invention claimed is: 1. A turbine engine convergent-divergent propulsion nozzle comprising: an annular central element and an annular cap arranged coaxially around the annular central element so as to co-operate with the annular central element to define an annular flow channel for an engine gas stream, wherein between a throat section of the turbine engine convergent-divergent propulsion nozzle, which is the smallest cross-section of the annular flow channel, and an ejection section of the nozzle, which is a cross-section at a downstream end of the turbine engine convergent-divergent propulsion nozzle, an external profile of the annular central element and an internal profile of the annular cap in longitudinal section are modeled by curves, second derivatives of the curves relative to an axial position along the respective curve have respective radii that are identical in absolute value, and wherein the turbine engine convergent-divergent propulsion nozzle is a fixed nozzle in the annular flow channel. 2. The turbine engine convergent-divergent propulsion nozzle according to claim 1 , wherein the internal profile and the external profile in longitudinal section of the annular central element and of the annular cap are symmetrical about an axis of symmetry. 3. The turbine engine convergent-divergent propulsion nozzle according to claim 2 , wherein the axis of symmetry is inclined relative to a longitudinal axis of the engine and forms an angle with the longitudinal axis in a range of 5° to 20°. 4. A bypass turbojet comprising a turbine engine convergent-divergent propulsion nozzle according to claim 1 . 5. A turboprop comprising a turbine engine convergent-divergent propulsion nozzle according to claim 1 .
Assignees
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Classifications
Jet pipe walls, e.g. liners · CPC title
with front fan · CPC title
curved · CPC title
- F02K1/00Primary
Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto (rocket nozzles F02K9/97) · CPC title
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- What does patent US9683516B2 cover?
- A turbine engine convergent-divergent nozzle including an annular central element and an annular cap arranged coaxially around the central element to co-operate with the central element to define an annular flow channel for a gas stream from the engine. Between a throat section and an ejection section of the nozzle, the central element and the cap present respective internal profiles in longitu…
- Who is the assignee on this patent?
- Snecma
- What technology area does this patent fall under?
- Primary CPC classification F02K1/00. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Jun 20 2017 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 1 related publication on this page (citations in our corpus or others sharing the same primary CPC).