Gas Turbine Engine Having Fan Rotor Driven by Turbine Exhaust and with a Bypass

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(12) (io) Patent No.:

United States Patent US 9,352,843 B2

(45) Patent:

Suciu et al. Date of May 31,2016

(54) GAS TURBINE ENGINE HAVING FAN ROTOR (56) References Cited DRIVEN BY TURBINE EXHAUST AND WITH U.S. PATENT DOCUMENTS A BYPASS 3,146,590 A * 9/1964 Erwin .......................... 60/39.17 (71) Applicant: United Technologies Corporation, 3,176,934 A * 4/1965 Kappus ........................ 244/12.3 Hartford, CT(US) 3,279,192 A * 10/1966 Hull, Jr. et al. ................. 60/264 3,312,424 A * 4/1967 Kappus ........................ 244/12.5 (72) Inventors: Gabriel L. Suciu, Glastonbury, CT 3,335,976 A * 8/1967 Kappus ........................ 244/12.3 (US); Jesse M.Chandler, South 3,366,350 A * 1/1968 Hoffert et al.................... 244/55 3,517,509 A * 6/1970 Bayati .......................... 60/226.1 Windsor, CT(US) 3,659,422 A * 5/1972 Hope .............................. 60/224 4,149,374 A * 4/1979 Barchenko ...................... 60/225 (73) Assignee: United Technologies Corporation, 4,254,619 A 3/1981 Giffin Hartford, CT(US) 4,462,206 A 7/1984 Aguet 4,679,394 A 7/1987 Taylor (*) Notice: Subject to any disclaimer, the term ofthis 4,996,836 A 3/1991 Reh et al.

5,778,659 A 7/1998 Duesler patent is extended or adjusted under 35 5,966,525 A 10/1999 Manzi U.S.C. 154(b) by 500 days.

6,260,800 B1 7/2001 Snell 6,409,469 B1 6/2002 Tse (21) Appl. No.: 13/731,371 6,439,840 B1 8/2002 Tse 6,837,038 132 * 1/2005 Eiler et al. ................... 60/226.1 (22) Filed: Dec. 31,2012 6,845,606 132 * 1/2005 Franchet et al. ................ 60/225 6,926,232 132 * 8/2005 Franchet et al. ............ 244/53 B 7,107,756 132 9/2006 Rolt (65) Prior Publication Data 8,015,796 132 9/2011 Babu et al.

2012/0128487 Al* 5/2012 Eames .............................. 416/1 US 2014/0183296 Al Jul. 3, 2014 * cited by examiner (51) Int. Cl.

B64D 27/00 (2006.01) Primary Examiner Philip J Bonzell B64D 27/14 (2006.01) (74) Attorney, Agent, or Firm Carlson, Gaskey & Olds F02K 3/02 (2006.01) F02K 3/06 (2006.01) (57) ABSTRACT F02K 3/077 (2006.01) B64D 27/02 (2006.01) A gas turbine engine has a core engine incorporating a core (52) U.S. Cl.

engine turbine.A fan rotor is driven by afan rotor turbine. The CPC ................ B64D 27/14(2013.01); B64D 27/02 fan rotor turbine is in the path of gases downstream from the (2013.01); F02K 3/025(2013.01); F02K 3/06 core engine turbine.A bypass door is moveablefrom a closed (2013.01); F02K 3/077(2013.01) position at which the gases from the core engine turbine pass (58) Field of Classification Search over the fan rotor turbine, and moveable to a bypass position CPC ........ B64D 33/00; B64D 33/04; B64D 27/10; at which the gases are directed away from the fan rotor tur- B64D 27/14; B64D 2027/026; B64D 2027/02; bine. An aircraft is also disclosed.

FOLD 17/105; F02K 3/04; F02C 9/18 See application file for complete search history. 5 Claims,3 Drawing Sheets r,1

Patent Sheet 1 of U.S. May 31,2016 3 US 9,352,843 B2

Patent Sheet 2 of B2

U.S. May 31,2016 3 US 9,352,843

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US 9,352,843 B2

GAS TURBINE ENGINE HAVING FAN ROTOR In another embodiment according to any of the previous DRIVEN BY TURBINE EXHAUST AND WITH embodiments, the core engine turbine drives a generator to A BYPASS generate electricity.

In another embodiment according to any of the previous STATEMENT REGARDING FEDERALLY 5 embodiments,the core engine also includes a compressor and SPONSORED RESEARCH OR DEVELOPMENT a combustor.

In another featured embodiment, an aircraft has an aircraft This invention was made with government support under body mounting a gas turbine engine. The gas turbine engine NASA Cooperative Agreement No. NNXIIAB35A. The includes a core engine incorporating a core engine turbine. A Government has certain rights in this invention. fan rotor is driven by a fan rotor turbine, and is in the path of gases downstream from the core engine turbine, and a bypass BACKGROUND OF THE INVENTION door. The bypass door is moveable from a closed position at which the gases from the core engine turbine pass over thefan This application relates to an arrangement where a gas 15 rotor turbine, and moveable to a bypass position at which the turbine engine can bypass a drive for a propulsor.

gases are directed away from the fan rotor turbine.

Gas turbine engines are known, and have typically In another embodiment according to the previous embodi- included a fan delivering air into both a bypass duct as pro- ment, there are a pair of fan rotors each driven by the gases pulsion, and into a core engine. The air leading into the core from a single core engine turbine.

engine is compressed in a compressor section, mixed with In another embodiment according to any of the previous fuel in a combustor section, and ignited. Products of this embodiments,the fan rotor turbine is positioned at a radially combustion pass downstream over turbine rotors, driving outer location on the fan rotor.

them to rotate. The turbine rotors in turn mechanically drive In another embodiment according to any of the previous the fan and compressor.

embodiments, a manifold receives the gases downstream of While this basic arrangement has proven successful,future 25 the core engine turbine and delivers the gases across both of aircraft designs require more flexibility.

the fan rotor turbines.

In addition, most gas turbine engines have a very large fan In another embodiment according to any of the previous delivering a high volume of air through the bypass duct, and embodiments,a rotational axis ofeach fan rotor, and the core rearwardly ofthe aircraft. This makes it difficultto operate the engine turbine are all offset relative to each other.

engines while the aircraft is sitting at an airport gate. Thus, it In another embodiment according to any of the previous is known to provide an auxiliary power unit (APU) on an embodiments, an actuator drives the bypass door to an open aircraft to provide power prior to starting the main gas turbine position.

engine for the aircraft. The APU is essentially a small gas In another embodiment according to any of the previous turbine engine that is relied upon to provide power such as embodiments, the bypass door is driven to the open position from electrical generators prior to the main gas turbine engine 35 when an aircraft receiving the gas turbine engine is at an starting.

airport gate.

In another embodiment according to any of the previous SUMMARY OF THE INVENTION embodiments, the core engine turbine drives a generator to generate electricity.

In a featured embodiment, a gas turbine engine has a core 40 In another embodiment according to any of the previous engine incorporating a core engine turbine. A fan rotor is embodiments,the core engine also includes a compressor and driven by a fan rotor turbine, and is in the path of gases a combustor.

downstream from the core engine turbine. A bypass door is In another embodiment according to any of the previous moveable from a closed position at which the gases from the embodiments, the aircraft body includes a tail. The gas tur- core engine turbine pass over the fan rotor turbine, and move- 45 bine engine is mounted on the tail.

able to a bypass position at which the gases are directed away These and other features of this application will be best from the fan rotor turbine.

understood from the following specification and drawings, In another embodiment according to the previous embodi- the following of which is a brief description.

ment, there are a pair offan rotors each driven by the gases from a single core engine turbine. 50 BRIEF DESCRIPTION OF THE DRAWINGS In another embodiment according to any of the previous embodiments, the fan rotor turbine is positioned at a radially FIG.1 shows an aircraft.

outer location on the fan rotor.

FIG.2shows an arrangement ofa gas turbine enginefor the In another embodiment according to any of the previous FIG. 1 aircraft.

embodiments, a manifold receives the gases downstream of 55 FIG.3 is an exploded view ofa portion ofthe FIG.2engine.

the core engine turbine and delivers the gases across both of FIG. 4 shows further detail.

the fan rotor turbines.

FIG.5A shows a bypass feature.

In another embodiment according to any of the previous FIG.5B shows a bypass feature actuated.

embodiments, a rotational axis ofeach fan rotor, and the core engine turbine are all offset relative to each other. 60 DETAILED DESCRIPTION In another embodiment according to any of the previous embodiments, an actuator drives the bypass door to an open An aircraft 20 has a tail area 126 provided with a pair of position. twin propulsor units 22 and 24. The propulsor units include a In another embodiment according to any of the previous fan rotor that will drive a large volume of air to provide embodiments, the bypass door is driven to the open position 65 propulsion for the aircraft.A single gas turbine core engine,or when an aircraft receiving the gas turbine engine is at an gas generator 26 will drive both propulsor units 22 and 24, as airport gate. explained below.

US 9,352,843 B2

3 4

As shown in FIG. 2, the core engine 26 includes a frame 254 moving an actuator shaft 256 to cause the bypass door 250 to pivot about a pivot point 252.

127 at a forward end mounting rotating parts of the engine.

The actuator includes a control and it is actuated to move Although shown schematically, a compressor section 128, a the door 250 to this bypass position when the additional combustor section 130, and a turbine section 132 are all 5 propulsion from thefan rotors 28 and 30is not desired.As one included in the core engine 26.Air passes into the compressor example, when the aircraft is sitting at a gate, by moving the section 128, the combustor section 130, and into the turbine bypass door 250 to the position illustrated in FIG.513,the gas section 132. The turbine section 132 drives the fan 28 and generator 26 may be operated to generate electricity such that compressor rotors (not shown) within compressor section the engine can replace the APU as typically required on 128.

current aircraft. Though the bypass feature is disclosed in a Air downstream of the turbine section 132 passes into a particular arrangement with twin propulsor units 22 and 24,it manifold 34, and will drive both propulsor units 22 and 24.A may have application in an arrangement where a single fan first propulsor unit 22 includes a fan rotor 30 received within rotor is driven by exhaust gas downstream of a turbine sec- a nacelle 51.The second propulsor unit 24 includes a fan rotor tion.

28 received within a nacelle 53. The right hand side ofFIG.2 15 Although an embodiment of this invention has been dis- is towards the rear ofthe aircraft 20(see FIG.1). Thus,the gas closed, a worker of ordinary skill in this art would recognize generator 26 extends forwardly ofthe propulsor units 22 and that certain modifications would come within the scope ofthis 24. One can appreciate rotational axes offan rotors 28 and 30 invention. For that reason, the following claims should be and the core engine 26 are all offset from each other.

studied to determine the true scope and content ofthis inven- As shown in FIG. 3, the exhaust from gas generator 26 is tion.

received within an opening 52 in the manifold 34, and there The invention claimed is: are flow distribution members 50 and 54 associated with the 1. An aircraft comprising: first 22 and second 24 propulsor units.

an aircraft body mounting a gas turbine engine, the gas As shown in FIG. 4, the fan rotor 28 has a shaft 129 turbine engine including a core engine incorporating a mounted within bearings 135, and the bearings are mounted 25 single core engine turbine, a pair offan rotors each being within static vanes 66 which are otherwise secured within a driven by a fan rotor turbine, and said fan rotor turbines nacelle 53. The vanes 66 are downstream of the rotor 28.

being in the path of gases downstream from said single Rotor 30 is mounted in a similar fashion.

core engine turbine, and a bypass door, said bypass door The distribution unit 54 delivers high pressure gas down- being moveable from a closed position at which the stream ofthe turbine section 132 across a tip turbine 55. The gases from the core engine turbine pass over said fan tip turbine 55 is driven to rotate by this gas, and in turn drives rotor turbine, and moveable to a bypass position at a ring 60. Ring 60 is fixed to a radially outer portion 62 ofthe which said gases are directed away from said fan rotor blades in the fan rotor 28. Thus, the turbine 55 drives the fan turbine; rotor 28 to rotate. The gases downstream ofthe tip turbine 55 wherein said bypass door is driven to said open position pass through an outlet 200 and communicate with an interior 35 when an aircraftreceiving said gas turbine engineis at an duct 202 within the nacelle 53, mixing with the air driven by airport gate; rotor 28.

said core engine turbine drives a generator to generate The single core engine or gas generator 26 is thus able to electricity; drive the twin propulsor units 22 and 24, and the overall said core engine also includes a compressor and a combus- arrangement fits within the package available on the aircraft tor; 20.

said aircraft body including a tail, and said gas turbine The gas turbine engine described to this point may be engine mounted on said tail; and generally as disclosed and claimed in co-pending patent the generation of electricity at an airport gate allows the application entitled "Twin Tip Turbine Propulsors Powered replacement of an auxiliary power unit.

By a Single Gas Turbine Generator," Ser. No. 13/662,879 45 2.The aircraft as setforth in claim 1, wherein said fan rotor filed on Oct. 29, 2012 with.

turbine is positioned at a radially outer location on said fan FIG.5A shows that a bypass door 250 may be incorporated rotor.

into the manifold 34. The bypass door 250 is shown in the 3. The aircraft as set forth in claim 2, wherein a manifold closed position in FIG. 5A, and the gas turbine engine will receives the gases downstream ofsaid core engine turbine and operate as disclosed above when the door 250 is in this posi- delivers the gases across both of said fan rotor turbines.

tion. Notably, a generator 240 is shown schematically pow- 4. The aircraft as set forth in claim 1, wherein a rotational ered by the turbine 132. The provision of a generator to be axis of each said fan rotor, and said core engine turbine all powered by a gas turbine engine turbine section is as known.

being offset relative to each other.

FIG. 5B shows the bypass door 250 moved to a bypass 5. The aircraft as set forth in claim 1, wherein an actuator position. Gases will pass at 260 away from the tip turbines 55 drives the bypass door to an open position.

(see FIG. 4). The rotors 28 and 30 will not be driven to rotate.

An actuator is illustrated schematically with an actuator drive