Gas turbine engine with bypass diverter means

Claim 2

A bypass gas turbine engine comprising an upstream fan; a core gas generator, comprising compressor means, combustion equipment and turbine means all in flow series, adapted to receive a core gas flow from the fan; a bypass duct adapted to receive a bypass flow from the fan; a first power turbine which is driven by the core gas after passing through the core gas generator; and bypass diverter means located within the bypass duct and adapted in a first mode to divert unheated bypass air to one or more augmentor wings and in a second mode to allow unheated bypass air to be directed to drive a second power turbine which is mechanically coupled to the first power turbine.

Claim 3

A bypass gas turbine engine as claimed in claim 1 wherein the variable bypass means comprises a changeover valve.

Claim 4

A bypass gas turbine engine as claimed in claim 1 wherein the second power turbine is situated radially outward of the first power turbine and is mounted thereon.

Claim 5

A bypass gas turbine as claimed in claim 1 wherein the first power turbine is situated radially outward of the second power turbine and is mounted thereon and the engine further comprises intermeshing passageways provided to direct a radially inner core flow to the first power turbine and to direct a radially outer bypass flow to the second power turbine.

Claim 6

A bypass gas turbine engine as claimed in claim 1 further comprising a variable area final exhaust nozzle situated downstream of the first power turbine through which the core flow is passed.

Claim 7

A compound helicopter comprising: at least one augmentor wing; and at least one bypass gas turbine engine comprising an upstream fan; a core gas generator, comprising compressor means, combustion equipment and turbine means all in flow series, adapted to receive a core gas flow from the fan; a bypass duct adapted to receive a bypass flow from the fan; a first power turbine which is driven by the core gas after passing through the core gas generator; and bypass diverter means located within the bypass duct and adapted in a first mode to divert unheated bypass air to said at least one augmentor wing and in a second mode to allow unheated bypass air to be directed to drive a second power turbine which is mechanically coupled to the first power turbine.

Claim 8

A compound helicopter comprising: at least one augmentor wing; and at least one bypass gas turbine engine comprising an upstream fan; a core gas generator, comprising compressor means, combustion equipment and turbine means all in flow series, adapted to receive a core gas flow from the fan; a bypass duct adapted to receive a bypass flow from the fan; a first power turbine which is driven by the core gas after passing through the core gas generator; and bypass diverter means located within the bypass duct and adapted in a first mode to divert unheated bypass air to said at least one augmentor wing and in a second mode to allow unheated bypass air to be directed to drive a second power turbine which is mechanically coupled to the first power turbine.

Claim 9

A bypass gas turbine engine comprising an upstream fan; a core gas generator, comprising compressor means, combustion equipment and turbine means all in flow series, adapted to receive a core gas flow from the fan; a bypass duct adapted to receive a bypass flow from the fan; a first power turbine which is driven by the core gas after passing through the core gas generator; and bypass diverter means located within the bypass duct and adapted in a first mode to divert bypass air to one or more augmentor wings and in a second mode to allow bypass air to be directed to drive a second power turbine which is mechanically coupled to the first power turbine; wherein the first power turbine is situated radially outward of the second power turbine and is mounted thereon and the engine further comprises intermeshing passageways provided to direct a radially inner core flow to the first power turbine and to direct a radially outer bypass flow to the second power turbine.

Claim 10

A bypass gas turbine engine comprising an upstream fan; a core gas generator, comprising compressor means, combustion equipment and turbine means all in flow series, adapted to receive a core gas flow from the fan; a bypass duct adapted to receive a bypass flow from the fan; a first power turbine which is driven by the core gas after passing through the core gas generator; and bypass diverter means located within the bypass duct and adapted in a first mode to divert bypass air to one or more augmentor wings and in a second mode to allow bypass air to be directed to drive a second power turbine which is mechanically coupled to the first power turbine; wherein the first power turbine is situated radially outward of the second power turbine and is mounted thereon and the engine further comprises intermeshing passageways provided to direct a radially inner core flow to the first power turbine and to direct a radially outer bypass flow to the second power turbine.