US 2003/0200754 A1 · Flow divider & purge air system for a gas turbine engine

Abstract

A purge air and fuel flow divider module (15) independently directs fuel flow to a plurality of manifolds (25, 27 and 29) and independently purges fuel from these manifolds with air when they are not flowing fuel. A secondary manifold (29) is filled with fuel before flowing metered burn flow to it and fuel flow is apportioned between a primary manifold (27) and the secondary manifold (29) during secondary manifold metered burn flow. Three manifolds are disclosed, a primary manifold (27), a secondary manifold (29) and a start or pilot manifold (25), each containing fuel nozzles (31, 33). A manifold main housing (61) contains a purge valve (41) and two three-way solenoids (37, 39) controlling respectively a secondary transfer valve (43) and a pilot nozzle transfer valve (45). Depending on the requirements, the solenoids position the valves to either provide manifold fill fuel, burn flow fuel or purge air to their respective manifolds. When fuel is shut off to the manifold, the purge valve (41) is remotely commanded to purge the primary manifold (27) with air.

Claims17

Dependent claims

A process of operating a gas turbine engine having a plurality of fuel manifolds each having multiple fuel nozzles for supplying fuel to an engine combustion region, comprising the steps of:

commencing fuel flow to a pilot manifold and to a primary manifold;
starting the engine;
stopping fuel flow to the pilot manifold and purging remaining fuel from the pilot manifold;
selectively charging a secondary manifold with fuel and subsequently enabling fuel flow from the secondary manifold to the engine combustion region;
stopping fuel flow to the secondary manifold and subsequently purging fuel from the secondary manifold;
ceasing engine operation by stopping fuel flow to the primary manifold and thereafter purging fuel therefrom.

3 more elements

A gas turbine engine fuel supply system for selectively supplying fuel to a plurality of engine fuel manifolds, comprising:

a source of high pressure air;
a source of metered fuel;
a source of unmetered fuel at a pressure higher than that of the metered fuel;
a pilot nozzle valve operable in one condition to supply fuel from the unmetered fuel source to an engine start manifold during engine startup and in another condition to direct high pressure air from the air source to the start manifold to purge fuel from the start manifold;
and
a pilot nozzle control solenoid normally supplying unmetered pressure from the fuel supply system to control the pilot nozzle valve to said another condition, and energizable to supply pressure from the unmetered source to control the pilot nozzle valve to said one condition where unmetered fuel flows through the control solenoid and through the pilot valve to the start manifold.

3 more elements

Dependencies are inferred from the claim text.

Flow divider & purge air system for a gas turbine engine

Life of this patent

Flow divider & purge air system for a gas turbine engine

Life of this patent

Abstract

Claims17