US3810360A - Gas generator with selectively connectible turbine system - Google Patents

Gas generator with selectively connectible turbine system Download PDF

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Publication number
US3810360A
US3810360A US00299279A US29927972A US3810360A US 3810360 A US3810360 A US 3810360A US 00299279 A US00299279 A US 00299279A US 29927972 A US29927972 A US 29927972A US 3810360 A US3810360 A US 3810360A
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Prior art keywords
turbine system
arrangement according
section
gas generator
critical cross
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Expired - Lifetime
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US00299279A
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English (en)
Inventor
H Leibach
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MTU Aero Engines AG
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MTU Motoren und Turbinen Union Muenchen GmbH
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/075—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type controlling flow ratio between flows
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/025—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the by-pass flow being at least partly used to create an independent thrust component

Definitions

  • ABSTRACT An engine arrangement for use with a vertical/short takeoff and landing airplane having a.v gas generator supplying exhaust gases selectively to a turbine system and to a thrust nozzle.
  • the turbine system is connectible to auxiliary lift devices, such as a lift rotor, for effecting vertical lift operations while the thrust nozzle is designed for normal cruising operations.
  • the flow of exhaust gases to the turbine system and the thrust nozzle is controlled such that the total cross-sectional area, with respect to the exhaust gas flow, of both the turbine system and the' thrust nozzle is maintained constant for all operations.
  • Sliding members are ar- 7 34 Claims, 3 Drawing Figures PATENTEBHAY 14 I974 SHEET 2 [IF 3 PATENTEDHAY 14 I974 SHEET 3 [IF 3 GAS GENERATOR WITH SELECTIVIELY CONNECTIBLE TURBINE SYSTEM BACKGROUND AND SUMMARY OF THE INVENTION
  • the present invention relates to an engine arrangement having a gas generator, a selectively connectible turbine system chargeable with the exhaust gases of the gas generator, and a selectively connectible thrust nozzle operated by the exhaust gases.
  • the present invention specifically relates to devices rendering the critical cross section of an opened thrust nozzle, when the turbine system is not under load, substantially identical with a critical through-flow cross section of the turbine system, when the exhaust gas load on the nozzle is released, or vice versa
  • the guide vanes of the turbine can constitute the critical gas cross section; when the nozzle is opened for horizontal flight, the nozzle aperture forms the critical cross section.
  • the present invention contemplates that, for transitional operation, i.e., when an airplane changes from vertical flight to horizontal flight, with the gas load being shifted from the utility turbine to the nozzle, the sum totals of the critical cross sections should be constant, so that the gas generator, with respect to its design, can always be utilized in the optimum operating range. In such a system, the gas generator does not tolerate any too large deviations from the sum of the two critical gas cross sections for the flow of exhaust gases without impairment of the gas generator operation.
  • governor of the utility turbine as adjustable, which design permits a variation of the critical cross section in a certain range.
  • this governorcontrol means doubtlessly will not be able to block the cross section entirely at the corresponding number of guide vanes,-for mechanical reasons, so that there is always a certain gas permeability. This means, in addition to thermal loads on the governor, that 'a mass flow loss will be experienced in case of a fully opened nozzle.
  • the present invention contemplates eliminating the disadvantages mentioned above in connection with gas generator composite systems, and has the object of constructing such a system so that it is possible in a relatively simple manner, i.e., also by relatively simple means, .to change over from pure nozzle operation (propulsive thrust) to utility turbine operation (vertical thrust),.while ensuring that the gas outlet area of the gas generator is always maintained substantially constant in the intermediate and final shifting phases.
  • the devices provided according to the present invention shall furthermore make it possible, when the noz-v zle or the turbine system (utility turbine) is not under load, to establish a flawless, loss-free seal and to provide for example when the turbine system is closed and the nozzle is opened an aerodynamically favorable guidance of the gaseous stream to the nozzle.
  • these'devices are to be operable by relatively minor adjusting forces.
  • the invention contemplates essentially, in order to solve the posed problem, to fashion the devices from rotationally symmetrically disposed slides, wherein a first slide controls the critical cross sectional area of the nozzle and a second slide controls the critical feed cross section of the turbine system.
  • the slides are to be operable by means of a common control device in such a manner that the second slide closes the critical cross sectional area of the turbine system to the same extent as the first slide opens the critical cross section of the nozzle, or vice versa.
  • FIG. 2 is a schematic longitudinal sectional view of a second embodiment of an engine arrangementin ac? cordance with a second embodiment of the present invention.
  • FIG. 3 is a schematic longitudional sectional view of I a third embodiment of an engine arrangement inaccordance with a third embodiment of the present invention.
  • the gas generator G illustrated in FIG. 1 comprises successively from the lefthand to the righthand side a three-stage axial-flow compressor 1, an annular combustion chamber 3 disposed coaxially to the longitudinal axis 2 of the gas generator G, and an adjoining single-stage turbine4.
  • the rotor 5 of the turbine 4 is connected to the rotors 7, 8, 9 of the axial-flow compressor l by way of a common shaft 6.
  • the exhaust gases conveyed by the gas generator G pass, after having been conducted past supporting guide blades 10, into an annular collecting chamber 1 l and place a single-stage turbine system 13 under load after being conducted through an annular feed duct 12, when a first cylindrical slide 14 closes the critical cross section F of a thrust nozzle 15, i.e., when a further annular duct 16 surrounding the turbine system 13 is blocked.
  • nozzle 15 is closed, a critical passage cross section-F, of the turbine system 13 is opened, namely by means of a second cylindrical slide 17 (final position, shown in dashed lines) to communicate the exhaust gases to the turbine system 13.
  • the first cylindrical slide 14 With the nozzle 15 being fully opened, the first cylindrical slide 14 is shifted into the position shown in full lines, so that the critical cross section F: of the nozzle I5 is essentially formed approximately between a terminal edge 18 of the slide 14 and a terminal edge'19 of an annular jacket 20 surrounding the turbine system 13.
  • the critical crosssectional area F, of the turbine system 13 is blocked, this area F, being formed between a terminal edge 21 of the second slide 17 and a divergent wall section 22 of an inner central element (the position of the second slide 17 shown in full lines).
  • the first slide 14 and the second slide 17 are operable, via a common steering unit '23, in such a manner that the sum of the openings at the critical cross sections F, plus F remains constant. That is, the critical cross sectional area F, of the turbine system 13 is opened to the same extent as the critical cross section F, of the nozzle is blocked, or vice versa.
  • the crosssectional widening from F, to F provided by the guide mechanism or diffuser 24 of the turbine system 13 and any power loss resulting therefrom do not play any appreciable role, especially when the useful output to be derived from the turbine system 13 is to be made available, for example, for driving a lift rotor which is not further illustrated in the drawings.
  • the shaft 25 of the turbine system 13 is in power connection with a drive shaft 27 leading to the lift rotor via a miter gear 26.
  • control device 23 By means of the control device 23, the respective relative motion of the first and second slides 14, 17 can be picked up via levers 28, 29 and connected linkages 30, 3l, by means of commonly driven shafts and cams attached thereto (not shown).
  • the control device 23 can be driven pneumatically, i.e., by an air motor fed, for example, with air tapped from the compressor 1 of the gas generator G.
  • FIG. 2 deviates from that of FIG. I essentially in that the critical cross-sectional area F, of the turbine system 13' is formed between the outer wall section 32 ofa feed duct 33 and a terminal section 34 of the second slide 35.
  • the second slide 35 in FIG. 2 is shaped in the form ofa central element provided with a curved wall section 36 in order to conduct the gases in an aerodynamically favorable manner to the turbine system 13' or the nozzle 15.
  • FIG. 2 is identical to that of FIG. 1 with respect to its mode of operation, so that the explanations set forth in connection with FIG. 1 apply in this respect, including the reference numerals.
  • the turbine system 37 inclusive of the devices (inter alia, second slide 38) for controlling the critical cross-sectional area F, thereof, is disposed in a plane spatially offset with respect to the plane of the gas generator G and the nozzle 39.
  • the critical through-flow cross section F, of the turbine system 37 is set essentially between a terminal edge 40 of the second slide 38 and a wall 42 externally defining the feed duct 41 or an inner sealing strip 43 pertaining to this wall.
  • the critical cross section F, of the nozzle .39 is adjusted essentially between the convergent wall 44 of a mushroom-shaped first slide 45 shaped in a divergentconvergent manner, and the outer jacket 46 and/or a sealing strip 46 of a nozzle duct 47.
  • a drive motor 48 drives the central shaft 51 via a shaft 49 and a bevel gear 50, and thus the first slide 45, engaging this shaft 51 by means of a spindle 52 thereof,
  • the central shaft 51 produces, via a further bevel gear 54, a rotational movement of the shaft 55 oriented to the turbine system 37; the spindle 56 of this shaft causes the second slide 38 engaging this spindle to move from the position shown in dashed lines into the position illustrated in full lines, whereby the critical cross-sectional area F, is made available.
  • the turbine system 37 which is thereby under the load of exhaust gases of the gas generator G (see also FIGS. 1 and 2) can, for example, drive a lifting jet (not illustrated) via shaft 57 and/or the gases exiting from the turbine system 37 can be fed to a pivotably mounted elbow-shaped auxiliary nozzle 58, for example in order to produce differential lateral thrust components for controlling the airplane.
  • An engine arrangement comprising: gas generator means for supplying exhuastgases,
  • a turbine system arranged downstream of said gas generator means, said turbine system having a first inlet for accepting said exhaust gases to drive said turbine system, said first inlet having a first critical cross-section corresponding to optimum driving of said turbine system by said exhaust gases,
  • a thrust nozzle arranged downstream of said gas generator means, said thrust nozzle having a second inlet for accepting said exhaust gases, said second inlet having a second critical cross-section corresponding to optimum operation of said thrust nozzle by said exhaust gases,
  • first inlet blocking means for selectively varying the inlet opening at said first critical cross-section
  • control means interconnecting said first and second inlet blocking means such that opening of said first critical cross-section results in simultaneous closing of said second critical cross-section and a closing of said first critical cross-section results in simultaneous opening of said second critical crosssection
  • first and second critical cross sections are annular shaped, and wherein said first and second inlet blocking means are constructed as respective rotationally symmetrical first and second slide members.
  • said first inlet blocking means includes means for varying the opening at said first critical cross section from an extreme open position corresponding to optimum operation of said turbine system utilizing all of said exhaust gases to an extreme closed position corresponding to complete shutdown of said turbine system utilizing none of said exhaust gases
  • said second inlet blocking means includes means for varying the opening at said second critical cross section from an extreme open position corresponding to optimum operation of said thrust nozzle utilizing all of said exhaust gases to an extreme closed position corresponding to a complete shutdown of said thrust nozzle utilizing none of said exhaust gases
  • said control means includes means for placing said first inlet blocking means in said closed position when said second inlet blocking means is in said open position and for placing said first inlet blocking means'in said open position when said second inlet blocking means is in said closed position.
  • control means includes a common control device for moving said slide members in such a manner that closing movement of one of said slide members is accompanied by a similar opening movement of the other of said slide members, whereby the total cross sectional area at said first and second cross sections remains constant for all operating conditions of the turbine system and thrust nozzle.
  • said first critical cross section is formed between a di- .vergent wall section of an inner central element of the turbine system and a terminal edge of said first slide member.
  • said first slide member is shaped inthe form of a central element provided with a curved wall section for aerodynamically guiding said exhaust gases to one of said turbine system and thrust nozzle.
  • said gas generator means includes a turbine and compressor unit mounted for rotation on a gas generator shaft, wherein said turbine system includes a turbine wheel mounted for rotation on a turbine system shaft, and wherein said turbine system shaft and said gas generator shaft extend along a common axis.
  • said first critical cross section is formed between a divergent wall section of an inner central element of the turbine system and a terminal edge of 'said first slide member.
  • said first slide member is shaped in the form of a central element provided with a curved wall section for aerodynamically guiding said exhaust gases to one of said turbine system and thrust nozzle.
  • said gas generator means includes a turbine and compressor unit mounted for rotation on a gas generator shaft, wherein said turbine system includes a turbine wheel mounted for rotation on a turbine system shaft, and wherein said turbine system shaft and said gas generator shaft extend along a common axis.
  • said gas generator means includes a turbine and compressor unit mounted for rotation on a gas generator shaft, wherein said turbine system includes a turbine wheel mounted for rotation on a turbine system shaft, and wherein said turbine system shaft is angularly disposed with respect to said gas generator shaft.
  • control means includes a common drive motor drivingly connected to said first and second slide members by way of shafts and spindles.
  • control means includes a common drive motor drivingly connected to said first and second slide members by way of shafts and spindles.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
US00299279A 1971-10-20 1972-10-20 Gas generator with selectively connectible turbine system Expired - Lifetime US3810360A (en)

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DE2152207 1971-10-20

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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4193262A (en) * 1977-02-24 1980-03-18 Rolls-Royce Limited Gas turbine engines
US4592508A (en) * 1983-10-27 1986-06-03 The Boeing Company Translating jet engine nozzle plug
US4598543A (en) * 1985-02-06 1986-07-08 The United States Of America As Represented By The Secretary Of The Air Force Variable cycle engine for high altitude aircraft
US20020189230A1 (en) * 2001-06-14 2002-12-19 Snecma Moteurs Variable cycle propulsion system with gas tapping for a supersonic airplane, and a method of operation
EP1302640A3 (en) * 2001-10-16 2006-08-09 United Technologies Corporation Variable cycle boost propulsor
US20100170221A1 (en) * 2009-01-08 2010-07-08 Toyota Jidosha Kabushiki Kaisha Turbo fan engine
US20120034080A1 (en) * 2007-11-29 2012-02-09 Agrawal Rajendra K Actuation mechanism for a convertible gas turbine propulsion system
US20120294719A1 (en) * 2011-05-18 2012-11-22 Rolls-Royce Plc Vertical lift fan
US20130341930A1 (en) * 2010-12-10 2013-12-26 Corporation Mc2 Recherches Internationales Turbine assembly, and kit with components for assembling the same

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB8927784D0 (en) * 1989-12-08 1990-05-30 Westland Helicopters Helicopters
DE4025567A1 (de) * 1990-08-11 1992-02-13 Daimler Benz Ag Gasturbine mit einem bypass im nutzleistungsturbinenteil
FR3055356A1 (fr) * 2016-08-30 2018-03-02 Guillaume Thomas Pelcot Turbomachine a deux turbines motrices libres et independantes ainsi que son dispositif de permutation entre ses deux modes de fonctionnement

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2507657A (en) * 1948-07-21 1950-05-16 Wiessler Gaston Antoin Auguste Aircraft with mixed type propulsion and sustaining means
US2587649A (en) * 1946-10-18 1952-03-04 Pope Francis Selective turbopropeller jet power plant for aircraft
US3255584A (en) * 1962-08-18 1966-06-14 Daimler Benz Ag Two stage gas turbine propulsion jet unit with thrust diverting means
GB1099971A (en) * 1966-01-11 1968-01-17 Bristol Siddeley Engines Ltd Power plants of the gas turbine type for helicopter aircraft
US3366350A (en) * 1964-08-08 1968-01-30 Dornier Werke Gmbh Propulsion unit for aircraft
US3678690A (en) * 1970-07-10 1972-07-25 United Aircraft Corp Convertible composite engine

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2458600A (en) * 1942-01-26 1949-01-11 Rateau Soc Aerodynamic propelling means operating through direct reaction jet and scavenging

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2587649A (en) * 1946-10-18 1952-03-04 Pope Francis Selective turbopropeller jet power plant for aircraft
US2507657A (en) * 1948-07-21 1950-05-16 Wiessler Gaston Antoin Auguste Aircraft with mixed type propulsion and sustaining means
US3255584A (en) * 1962-08-18 1966-06-14 Daimler Benz Ag Two stage gas turbine propulsion jet unit with thrust diverting means
US3366350A (en) * 1964-08-08 1968-01-30 Dornier Werke Gmbh Propulsion unit for aircraft
GB1099971A (en) * 1966-01-11 1968-01-17 Bristol Siddeley Engines Ltd Power plants of the gas turbine type for helicopter aircraft
US3678690A (en) * 1970-07-10 1972-07-25 United Aircraft Corp Convertible composite engine

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4193262A (en) * 1977-02-24 1980-03-18 Rolls-Royce Limited Gas turbine engines
US4592508A (en) * 1983-10-27 1986-06-03 The Boeing Company Translating jet engine nozzle plug
US4598543A (en) * 1985-02-06 1986-07-08 The United States Of America As Represented By The Secretary Of The Air Force Variable cycle engine for high altitude aircraft
US7162859B2 (en) 2001-06-14 2007-01-16 Snecma Moteurs Variable cycle propulsion system with gas tapping for a supersonic airplane, and a method of operation
US20020189230A1 (en) * 2001-06-14 2002-12-19 Snecma Moteurs Variable cycle propulsion system with gas tapping for a supersonic airplane, and a method of operation
US6845606B2 (en) * 2001-06-14 2005-01-25 Snecma Moteurs Variable cycle propulsion system with gas tapping for a supersonic airplane, and a method of operation
US20050211822A1 (en) * 2001-06-14 2005-09-29 Snecma Moteurs Variable cycle propulsion system with gas tapping for a supersonic airplane, and a method of operation
EP1302640A3 (en) * 2001-10-16 2006-08-09 United Technologies Corporation Variable cycle boost propulsor
US20120034080A1 (en) * 2007-11-29 2012-02-09 Agrawal Rajendra K Actuation mechanism for a convertible gas turbine propulsion system
US9580183B2 (en) * 2007-11-29 2017-02-28 Sikorsky Aircraft Corporation Actuation mechanism for a convertible gas turbine propulsion system
US20100170221A1 (en) * 2009-01-08 2010-07-08 Toyota Jidosha Kabushiki Kaisha Turbo fan engine
US20130341930A1 (en) * 2010-12-10 2013-12-26 Corporation Mc2 Recherches Internationales Turbine assembly, and kit with components for assembling the same
US20120294719A1 (en) * 2011-05-18 2012-11-22 Rolls-Royce Plc Vertical lift fan

Also Published As

Publication number Publication date
GB1407428A (en) 1975-09-24
FR2156883B1 (en:Method) 1976-06-04
FR2156883A1 (en:Method) 1973-06-01

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