Low infrared signature exhaust through active film cooling active mixing and acitve vane rotation
US-2018149114-A1 · May 31, 2018 · US
Takeoff power boost
US11248552B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11248552-B2 |
| Application number | US-201916508673-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jul 11, 2019 |
| Priority date | Jul 11, 2019 |
| Publication date | Feb 15, 2022 |
| Grant date | Feb 15, 2022 |
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- Title
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- Abstract
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Abstract
Official abstract text for this publication.
Embodiments are directed to boosting aircraft engine performance for takeoff and critical mission segments by reducing airflow used for cooling exhaust gases. The airflow is reduced by stopping an accessory blower or by closing an external air vent. Eliminating the cooling airflow to the exhaust has the effect of lowering the backpressure on the engine, which thereby increases maximum engine power.
First claim
Opening claim text (preview).
What is claimed is: 1. A system for managing airflow in an engine exhaust, comprising: a turbine section of an engine configured to create a primary exhaust airflow during operation; an exhaust section coupled to the turbine section and configured to pass the primary exhaust airflow; a mixing section in the exhaust section, the mixing section configured to receive an accessory component airflow from an engine accessory component and to mix the accessory component airflow with the primary exhaust airflow; a blower configured to selectively provide the accessory component airflow to the mixing section; and a flight control computer configured to selectively turn the blower on in a response to determining accessory cooling is needed without regard to maximum engine power requirements and configured to selectively turn the blower off in response to determining maximum engine power is required. 2. The system of claim 1 , wherein the flight control computer is configured to determine the maximum engine power is required based upon one or more of aircraft configuration, aircraft flight status, and environmental conditions. 3. The system of claim 1 , wherein the engine accessory component is selected from a centrifugal blower, an oil cooler blower, and an engine particle separator (EPS). 4. The system of claim 1 , wherein the engine is configured to move between a horizontal position and a vertical position during operation, and wherein the blower is further configured to selectively provide the accessory component airflow based upon engine position.
Assignees
Inventors
Classifications
the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title
in helicopters · CPC title
by means of air pumps · CPC title
- F02K1/386Primary
mixing devices in the jet pipe, e.g. for mixing primary and secondary flow · CPC title
comprising infrared suppressors · CPC title
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Frequently asked questions
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- What does patent US11248552B2 cover?
- Embodiments are directed to boosting aircraft engine performance for takeoff and critical mission segments by reducing airflow used for cooling exhaust gases. The airflow is reduced by stopping an accessory blower or by closing an external air vent. Eliminating the cooling airflow to the exhaust has the effect of lowering the backpressure on the engine, which thereby increases maximum engine po…
- Who is the assignee on this patent?
- Bell Textron Inc, Textron Innovations Inc
- What technology area does this patent fall under?
- Primary CPC classification F02K1/386. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Feb 15 2022 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 3 related publications on this page (citations in our corpus or others sharing the same primary CPC).