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US 3,938,328 AGranted
Multicycle engine
AssigneeThe Boeing Company
InventorGarry W. Klees
Life of this patent
Estimating the term…
Abstract
Air breathing gas turbine engine design concepts, and methods and apparatus for providing variable engine cycles are disclosed. The preferred engine embodiments involve two flow control valve systems for internal management of air, each of which have the capacity to cross-over or invert adjacent annular flow patterns, and at least one of which is capable of switching from inverted to straight through flow.
Claims12
A turbine engine comprising:
- an inlet for guiding ambient fluid into said engine;
- a forwardly located compression means having blade elements for compressing fluid passing through said inlet;
- a centrally located core gas generator including compression, combustion and turbine stages;
- an aft turbine driveably connected to said forward compression means, and located downstream of said core gas generator for acting on fluid passing through said inlet;
- a first fluid flow control system positioned to receive fluid from said inlet and said blade elements and defining two adjacent annular flow patterns;
- and a second fluid flow control system positioned to receive fluid from said first fluid flow control system and said core gas generator and defining two adjacent annular flow patterns;
- said first and second fluid flow control systems each comprising means for inverting the respective positions of said two adjacent annular flow patterns between the entrance and exit ends of its system and within the confines of a passageway having an area substantially equal to the combined area of the two adjacent annular flow patterns at substantially all positions along its length between said entrance and exit ends.
4 more elements
A turbine engine comprising:
- an inlet for guiding ambient fluid into said engine;
- a forwardly located compression means having blade elements for compressing fluid passing through said inlet;
- a centrally located core gas generator including compression, combustion and turbine stages;
- an aft turbine, driveably connected to said forward compression means, and located downstream of said core gas generator for acting upon fluid passing through said inlet;
- a first fluid flow control system positioned to receive fluid from said inlet and said blade elements and defining two adjacent annular flow patterns;
- and a second fluid flow control system positioned to receive fluid from said first fluid flow control system and said core gas generator and defining two adjacent annular flow patterns;
- said first and second fluid flow control systems each comprising means for inverting the respective positions of said two adjacent annular flow patterns between the entrance and exit ends of the system;
- wherein at least one of said systems comprises means for switching the respective positions of said two flow patterns from their inverted positions at each of said entrance and exit ends.
5 more elements
Dependencies are inferred from the claim text.