초록 ▼

A gas turbine engine includes a compressor, combustor, and turbine having a row of blades mounted inside a surrounding turbine shroud. A heat exchanger is used for cooling pressurized air bled from the compressor. A distribution network joins the heat exchanger to the turbine for selectively channel

A gas turbine engine includes a compressor, combustor, and turbine having a row of blades mounted inside a surrounding turbine shroud. A heat exchanger is used for cooling pressurized air bled from the compressor. A distribution network joins the heat exchanger to the turbine for selectively channeling air from the heat exchanger below the blades and above the shroud for controlling blade tip clearance.

대표청구항 ▼

The invention claimed is: 1. A gas turbine engine comprising: a fan mounted inside a nacelle in serial flow communication with a compressor, combustor, high pressure (HP) turbine powering said compressor, and a low pressure turbine powering said fan; said HP turbine including a row of turbine rotor

The invention claimed is: 1. A gas turbine engine comprising: a fan mounted inside a nacelle in serial flow communication with a compressor, combustor, high pressure (HP) turbine powering said compressor, and a low pressure turbine powering said fan; said HP turbine including a row of turbine rotor blades mounted inside a surrounding turbine shroud, with a radial gap therebetween; a heat exchanger disposed in a fan bypass duct inside said nacelle in flow communication with said compressor for using fan air to cool pressurized discharge air from said compressor; and a distribution network disposed in flow communication with said heat exchanger, and including a plurality of valves for selectively distributing said compressor air to said HP turbine both outside said shroud and inside said blades. 2. An engine according to claim 1 further comprising: an active clearance control (ACC) mount supporting said shroud around said blades; said network having a first circuit joining said heat exchanger to said mount, and a second circuit joining said mount to said blades; and a controller operatively joined to said valves in said network for adjusting flow of said compressor air through said first and second circuits. 3. An engine according to claim 2 wherein said network further comprises: a first bypass joined in flow communication from said compressor to said mount to bypass said heat exchanger; and a second bypass joined in flow communication from said heat exchanger to said second circuit to bypass said mount. 4. An engine according to claim 3 wherein: said first bypass includes a first valve in serial flow communication therein for selectively controlling bypass flow therethrough; said second bypass includes a second valve in serial flow communication therein for selectively controlling bypass flow therethrough; and said first circuit includes a third valve in serial flow communication therein for selectively controlling flow therethrough. 5. An engine according to claim 4 wherein said controller is operatively joined to said first, second, and third valves and configured for adjusting flow therethrough in three different modes of operation respectively favoring flow through different ones of said three valves. 6. An engine according to claim 5 wherein said mount comprises: an annular case supporting a row of said turbine shrouds around said blades; and a plenum surrounding said case, and having an impingement baffle therein disposed in flow communication with said first circuit for impinging said air against said case to control radial expansion thereof. 7. An engine according to claim 6 wherein said blades include internal cooling channels disposed in flow communication with said second circuit, and said second circuit is joined in flow communication with said plenum for collecting spent impingement air from said case for flow to said blades. 8. An engine according to claim 7 further comprising: inner and outer combustor casings surrounding said combustor; and said second circuit includes a mixing chamber mounted below said inner casing, and a plurality of transfer tubes extending radially through said inner and outer casings in flow communication with said chamber. 9. An engine according to claim 7 further comprising: a diffuser disposed at the outlet of said compressor for diffusing compressor discharge air into said combustor, and joined to said heat exchanger; and a flow inducer disposed in said second circuit in flow communication between said chamber and blades for channeling air thereto. 10. A method of using said engine according to claim 7 comprising: opening said first valve in a first mode of operation for heating said case; opening said second valve in a second mode of operation to bypass said case; and opening said third valve in a third mode of operation to effect active clearance control of said gap by impinging air on said case. 11. A gas turbine engine comprising: a compressor, combustor, and high pressure turbine disposed in serial flow communication; said turbine including a row of turbine rotor blades mounted inside a surrounding turbine shroud, with a radial gap therebetween; a heat exchanger disposed in flow communication with said compressor for cooling pressurized air therefrom; and a compound distribution network disposed in flow communication with said heat exchanger and including valves for selectively distributing said cooled air to said turbine both below and inside said blades and above and outside said shroud for controlling magnitude of said radial gap. 12. An engine according to claim 11 wherein: said turbine further includes an annular case supporting a row of said turbine shrouds around said blades; and said network includes a first circuit joined in flow communication from said heat exchanger to said case for channeling said cooled air thereto, and a second circuit joined in flow communication from said case to said blades for channeling said air thereto. 13. An engine according to claim 12 wherein said network further comprises: a first bypass joined in flow communication from said compressor to said case to bypass said heat exchanger; and a second bypass joined in flow communication from said heat exchanger to said second circuit to bypass said case. 14. An engine according to claim 13 wherein: said first bypass includes a first valve in serial flow communication therein for selectively controlling bypass flow therethrough; said second bypass includes a second valve in serial flow communication therein for selectively controlling bypass flow therethrough; and said first circuit includes a third valve in serial flow communication therein for selectively controlling flow therethrough. 15. An engine according to claim 14 further comprising a controller operatively joined to said first, second, and third valves and configured for adjusting flow therethrough in three different modes of operation respectively favoring flow through different ones of said three valves. 16. An engine according to claim 14 wherein: said turbine further includes a plenum surrounding said case, and having an impingement baffle therein disposed in flow communication with said first circuit for impinging said air against said case to control radial expansion thereof; and said blades include internal cooling channels disposed in flow communication with said second circuit for cooling said blades. 17. An engine according to claim 16 wherein said second circuit is joined in flow communication with said plenum for collecting said spent impingement air from said case. 18. An engine according to claim 14 further comprising: a fan mounted inside a nacelle forward of said compressor and joined to a low pressure turbine following said high pressure turbine; said nacelle being spaced from said compressor to define a fan bypass duct therearound; and said heat exchanger is disposed in flow communication with said bypass duct for channeling fan air thereto to cool said compressor air. 19. An engine according to claim 14 further comprising: inner and outer combustor casings surrounding said combustor; and said second circuit includes a mixing chamber mounted below said inner casing, and a plurality of transfer tubes extending radially through said inner and outer casings in flow communication with said chamber. 20. An engine according to claim 19 wherein said second circuit further includes: a plurality of mixing holes disposed in said inner casing in flow communication between said compressor and chamber; and an annular flow inducer disposed in flow communication between said chamber and blades for channeling air thereto. 21. A method for effecting active clearance control (ACC) in a turbofan engine including in serial flow communication a fan, compressor, combustor, high pressure (HP) turbine, and a low pressure turbine comprising: cooling hot discharge air from said compressor in a heat exchanger cooled by air from said fan; channeling cooled air from said heat exchanger to an ACC mount in said HP turbine supporting a row of turbine shrouds around turbine blades; and channeling spent air from said mount to internal cooling channels inside said blades in one of plural selective different modes of active clearance control. 22. A method according to claim 21 further comprising bypassing said hot compressor discharge air around said heat exchanger directly to said mount. 23. A method according to claim 22 further comprising bypassing said cooled air from said heat exchanger around said mount directly to said blades. 24. A method according to claim 23 further comprising correspondingly adjusting flow of said air from said heat exchanger to said mount, and from said heat exchanger bypassing said mount, and from said compressor bypassing said heat exchanger in three different modes of operation including active clearance control on and off.