Method for operating a gas turbine installation and the same
US-2016377000-A1 · Dec 29, 2016 · US
Aircraft airflow modulation system and method
US9103280B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9103280-B2 |
| Application number | US-201313781584-A |
| Country | US |
| Kind code | B2 |
| Filing date | Feb 28, 2013 |
| Priority date | Aug 11, 2009 |
| Publication date | Aug 11, 2015 |
| Grant date | Aug 11, 2015 |
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Abstract
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The present invention relates to a mechanical system and method that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses two articulating components, a movable air flow duct and an articulating cone. The air flow duct, in a first position, is in exclusive air flow communication with the circular intake face of the turbine in a first position to receive air from the intake diffuser. In this configuration the expandable cone is in a retracted position and does not redirect airflow and allows the aircraft to operates in low speed mode as only the turbo jet receives airflow. In a transition speed mode, the air flow duct is retracted to allow air flow to both the turbo jet and the CVC. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face directing air solely to the high Mach aircraft engine to allow the aircraft to operate in high speed mode.
First claim
Opening claim text (preview).
What is claimed is: 1. A method of propelling an aircraft having an integrated turbine and a plurality of high Mach aircraft engines disposed about the integrated turbine, the integrated turbine defining a center shaft and a generally circular turbine intake face, the method comprising: positioning a translatable cylindrical air duct upstream of the turbine and high Mach aircraft engines, the cylindrical air duct being axially translatable with respect to the center shaft and posi…
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Cross-Sectional Technologies · mapped topic
Mechanical Engineering · mapped topic
- F02C7/042Primary
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
Mechanical Engineering · mapped topic
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- What does patent US9103280B2 cover?
- The present invention relates to a mechanical system and method that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses two…
- Who is the assignee on this patent?
- Northrop Grumman Systems Corp
- What technology area does this patent fall under?
- Primary CPC classification F02C7/042. Mapped technology areas include Mechanical Engineering.
- When was this patent published?
- Publication date Tue Aug 11 2015 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 8 related publications on this page (citations in our corpus or others sharing the same primary CPC).