Valve for diverting fluid flows in turbomachines

Patent · Tue May 13 04:00:00 EDT 1986

OSTI ID:5634671

Nightingale, D J; Ward, B D

A fluid flow diverter valve is described for a gas turbine engine of the type that comprises a fluid flow duct, first and second axial flow compressors spaced along the duct, a combustible means downstream of the compressors, turbine means downstream of the combustion means connected to the processors to drive the compressors, one or more air outlet openings in the duct wall of a region between the first and second compressors, and an auxiliary air intake in the duct wall spaced along the duct from the one or more outlet openings and located at a region between the one or more outlet openings and the second compressor. The valve consists of a hollow tubular sleeve extending co-axially along the duct, the sleeve being movable in directions along the duct, and being provided with one or more openings which in a first position of the sleeve uncover the auxiliary air intake in the duct wall; doors each of which is pivotally mounted at one of its ends on the sleeve, the doors being spaced around the axis of the duct and being shaped and positioned so that in a first position of the doors they lie along the length of the duct and at least one of the doors obturates the one or more openings in the sleeve and in a second position of the doors the free end of each door is moved radially inwards and each door co-operates with the other doors and thereby obturate the duct.

• Assignee: Rolls-Royce, Inc., New York, NY
• Patent Number(s): US 4587803
• OSTI ID: 5634671
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103* -- Internal Combustion Engines-- Turbine
ACTUATORS
AIR FLOW
COMPRESSORS
CONTROL EQUIPMENT
DUCTS
ENGINES
EQUIPMENT
FLOW REGULATORS
FLUID FLOW
GAS FLOW
GAS TURBINE ENGINES
HEAT ENGINES
INTERNAL COMBUSTION ENGINES
MACHINERY
POSITIONING
SLEEVES
SPACE DEPENDENCE
TURBINES
TURBOMACHINERY
VALVES