GB2155110A - High bypass ratio counter-rotating turbofan engine - Google Patents

High bypass ratio counter-rotating turbofan engine Download PDF

Info

Publication number
GB2155110A
GB2155110A GB08505193A GB8505193A GB2155110A GB 2155110 A GB2155110 A GB 2155110A GB 08505193 A GB08505193 A GB 08505193A GB 8505193 A GB8505193 A GB 8505193A GB 2155110 A GB2155110 A GB 2155110A
Authority
GB
United Kingdom
Prior art keywords
drive shaft
blade row
compressor
turbine
fan
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
GB08505193A
Other versions
GB8505193D0 (en
Inventor
Alan Roy Stuart
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of GB8505193D0 publication Critical patent/GB8505193D0/en
Publication of GB2155110A publication Critical patent/GB2155110A/en
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/03—Annular blade-carrying members having blades on the inner periphery of the annulus and extending inwardly radially, i.e. inverted rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D7/00—Rotors with blades adjustable in operation; Control thereof
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/66—Reversing fan flow using reversing fan blades
    • 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
    • F02K3/072—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 with counter-rotating, e.g. fan rotors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/74—Adjusting of angle of incidence or attack of rotating blades by turning around an axis perpendicular the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
    • F05D2260/76—Adjusting of angle of incidence or attack of rotating blades the adjusting mechanism using auxiliary power sources

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

A gas turbine engine comprises a gas generator 16 for generating combustion gases, a power turbine 30, a propulsor section 52, and a booster compressor 66, the power turbine including first and second counter rotatable turbine blade rows 38, 42 effective for rotating first and second drive shafts, 44, 48 respectively. The propulsor section includes a first propulsor blade row 58 connected to the first drive shaft and a second propulsor blade row 62 connected to the second drive shaft, the booster compressor including a first compressor blade row 70 connected to the first drive shaft 44 and a second compressor blade row 74 connected to the second drive shaft 48. Pitch adjustment of either or both propulsor blade rows, by for example unison rings, is disclosed (Fig. 56). <IMAGE>

Description

SPECIFICATION High bypass ratio counterrotating turbofan engine This invention relates to gas turbine engines and, more particularly, to a turbofan engine with a counterrotating low pressure system, and is related to the counterrotating turbofan proposed in the specification of British Patent Application No. 2 129 502, which was unpublished at the priority date hereof, but which will be referred to for the purpose of providing a better understanding of the present invention.
This previously proposed counterrotating turbofan is driven by a counterrotating power turbine. One of its features is the configuration of the power turbine and the ratio of the mean flowpath radius of such turbine to the mean flowpath radius of the gas generator. This is required in part to ensure lower fan tip speed and/or higher turbine blade speed.
Under certain design conditions, it may be desirable to reduce the mean flowpath radius of the power turbine. According to an embodiment shown in the above-mentioned specification, such a reduction in the mean flowpath radius of the power turbine would increase the fan tip speed thereby reducing the efficiency of the engine.
Objects of the invention It is an object of the present invention to provide a new and improved high bypass ratio counterrotating turbofan engine.
It is another object of the present invention to provide a new and improved turbofan engine with a cou nterrotating booster compressor.
It is yet another object of the present invention to provide a new and improved turbofan engine with forward mounted counterrotating fan and booster compressor driven by two counterrotating shafts.
It is still a further object of the present invention to provide a counterrotating turbofan engine with blade pitch actuation means effective for reversing fan flow.
Summary of the invention In accordance with the present invention, a gas turbine engine is disclosed. The engine comprises a gas generator effective for generating combustion gasses, a power turbine, a propulsor section, and a booster compresssor. The power turbine includes first and second counterrotatable turbine blade rows effective for rotating first and second drive shafts, respectively. The propulsor section includes a first propulsor blade row connected to the first drive shaft and a second propulsor blade row connected to the second drive shaft. The booster compressor includes a first compressor blade row connected to the first drive shaft and a second compressor blade row connected to the second drive shaft.
In a further embodiment of the present invention, the gas turbine engine further comprises blade pitch actuation means for varying the pitch of the second propulsor blade row. The actuation means are effective to reverse the propulsor flow.
Brief description of the drawings Figure lisa view of a high bypass ratio counterrotating turbofan engine according to one form of the present invention.
Figure 2 is a view of a booster compressor for a high bypasf ratio turbofan engine according to another form of the present invention.
Figure 3 is a view taken along the line 3-3 in Figure 1.
Figure 4 is a view of the fan blades shown in Figure 3 actuated to provide reverse fan flow.
Figure 5 is a view of a second row fan blade and actuation means according to one form of the present invention.
Figure 6 is a view taken from the direction of arrow 6 in Figure 5.
Detailed description of the invention Figure 1 shows a gas turbine engine 10 according to one embodiment of the present invention. Engine 10 includes a longitudinal center line axis 12 and an annular casing 14 disposed coaxiaily about axis 12.
Engine 10 also includes a core gas generator 16 which includes a compressor 18, a combustor 20, and a high pressure turbine 22, either single or multiple stage, all arranged coaxially about the longitudinal axis 12 of engine 10 in serial, axial flow relationship. An annular drive shaft 24 fixedly interconnects compressor 18 and high pressure turbine 22.
The gas generator 16 is effective for generating combustion gases. Pressurized air from compressor 18 is mixed with fuel in combustor 20 and ignited, thereby generating combustion gases. Some work is extracted from these gases by high pressure turbine 22 which drives compressor 18. The remainder of the combustion gases are discharged from the gas generator 16 through strut 26 of support member 28 and into power turbine 30. Strut 26 may include turbine inlet guide vanes.
Power turbine 30 includes a first annular drum rotor 32 rotatably mounted by suitable bearings 34 to frame hub member 36. First rotor 32 includes a plurality of first turbine blade rows 38 extending radially inwardly therefrom and axially spaced.
Power turbine 30 also includes a second annular drum rotor 40 disposed radially inwardly of first rotor 32 and first blade rows 38. Second rotor 40 includes a plurality of second turbine blade rows 42 extending radially ourwardly therefrom and axially spaced. Second rotor 40 is rotatably mounted to first shaft 44 by differential bearings 46.
Each of the first and second turbine blade rows 38 and 42 comprises a plurality of circumferentially spaced turbine blades, with the first blade rows 38 alternately spaced with respective ones of the second blade rows 42. Combustion gases flowing through the blade rows 38 and 42 drive first and second rotors 32 and 40 in counterrotating directions.
Fixedly attached to first and second rotors 32 and 40 are first and second drive shafts 44 and 48, respectively. Thus, first and second rotors 32 and 40 are effective for driving first and second drive shafts 44 and 48, respectively. Drive shafts 44 and 48 are coaxially disposed relative to center line 50 of engine 10 and extend forward through gas generator 16.
Engine 10 further comprises a forward fan section 52. Fan section 52 is disposed radially inwardly of annular fan duct 54 which is suitably secured by strut 56 to casing 14. Fan section 52 includes a first fan blade row 58 connected to the forward end 60 of first drive shaft 44. Similarly, fan section 52 includes a second fan blade row 62 connected to the forward end 64 of second drive shaft 48.
Each of the first and second fan blade rows 58 and 62 comprises a plurality of circumferentially spaced fan blades. Fan blade rows 58 and 62 are counterrotating which provides a relatively high fan efficiency and propulsive efficiency with generally low absolute tip speed on each fan blade row.
Engine 10 further comprises a booster compressor 66. Booster compressor 66 includes a first annular rotor 68 including a plurality of first compressor blade rows 70 extending radially outwardly therefrom and axially spaced. Booster compressor 66 also includes a second annular rotor 72 disposed radially outwardly of rotor 68 and first compressor blade rows 70. Rotor 72 includes a plurality of second compressor blade rows 74 extending radially inwardly therefrom and axially spaced. Rotor 68 is fixedly attached to fan blade row 58 and a forward end 60 of first drive shaft 44.
similarly, rotor 72 is fixedly attached to fan blade row 62 and the forward end 64 of second drive shaft 48.
Each of the first and second compressor blade rows 70 and 74 comprises a plurality of circumferentially spaced compressor blades, with the first blade rows 70 alternately spaced with respective ones of the second blade rows 74.
Compressor blade rows 70 and 74 are counterrotating and located in the core duct 76 leading into compressor 18 of gas generator 16.
The counterrotating booster compressor 66 provides a significant pressure rise to air entering the core gas generator 16. An advantage of having the fan blade row and the compressor blade rows driven by the same drive shaft is that energy is optimally extracted from power turbine 30. Without the booster compressor stages being driven by the power turbine from shafts 44 and 48, a separate compressor with an additional shaft and drive turbine would be required. Furthermore, if the booster compressor stages were non-existent, the engine would be limited in overall pressure ratio resulting in poorer efficiency. By having compressor blade rows 70 and 74 counterrotating, a lesser number of compressor blade rows than that required for a single low speed compressor driven from only one shaft is possible.
Figure 2 shows an alternative embodiment of fan section 52 and booster compressor 66. Booster compressor 66 is configured so that rotor 68 is disposed radially outwardly from rotor 72, Thus, first compressor blade rows 70 extend radially inwardly from rotor 68 and compressor blade rows 74 extend radially outwardly from rotor 72.
Figure 3 is a view taken along the line 3-3 in Figure 1 . It shows a typical pitch angle of fan blades of first and second fan blade rows 58 and 62, respectively. The direction of motion of fan blade row 58 is shown by arrow 78 and the direction of fan blade row 62 is shown by arrow 80. The counterrotation of fan blade rows 58 and 62 is effective to produce a fan flow 82 in an axially aft direction thereby producing forward thrust.
By varying the pitch setting for either or both of fan blade rows 58 and 62, it is possible to reverse fan flow 82. Figure 4 shows a configuration wherein the blades in the second fan blade row 62 have been actuated to a different pitch effective to reverse fan flow. It should be noted that such actuation of the blades in the second fan blade row 62 may produce a flow sufficient to reverse the direction 78 of first fan blade row 58. However, the motion of rows 58 and 62 will remain differential as shown by the relative magnitudes of arrows 78 and 80 in Figure 4.
Various mechanisms are possible to provide actuation to the fan blades. Figures 5 and 6 show one such mechanism. Figure 5 shows a fan blade 84 with hub 86. Blade pitch actuation means 88 are shown in more detail in Figure 6. Blade pitch actuation means 88 includes piston ring 90, flange member 92, first and second actuator arms 94 and 96, and unison ring 98. Flange member 92 is fixedly attached at one end to piston ring 90 and pivotally connected at its other end to first actuation arm 94.
Actuator arms 94 and 96 are joined and second actuator arm 96 is pivotally joined to unison ring 98.
Hub 86 of blade 84 is fixedly attached to first actuating arm 94. As piston ring 90 is pneumatically actuated and moves generally axially along line 100 to a position shown by phantom lines 101, fan blade 84 will rotate about its axis. At the same time, unison ring 98 will rotate to a position shown by phantom lines 102, thereby ensuring that all other blades on the fan blade row are in unison.
It will be clearto those skilled in the artthatthe present invention is not limited to the specific embodiments illustrated herein. Nor is the invention limited to a turbofan configuration. Rather, the invention applies in a broader sense to engines with counterrotating propulsor blades such as an unducted fan or propeller.
It will be understood that the dimensions and proportional and structural relationships shown in the drawings are illustrated by way of example only and those illustrations are not to be taken as the actual dimensions or proportional structural relationships used in the counterrotating tubofan engine of the present invention.
Numerous modifications, variations, and full and partial equivalents can be undertaken without departing from the invention as limited only by the spirit and scope of the appended claims.

Claims (8)

1. A gas turbine engine comprising: a gas generator effective for generating combustion gases; a power turbine including first and second counterrotatable turbine blade rows effective for rotating first and second drive shafts, respectively; a propulsor section including a first propulsor blade row connected to said first drive shaft and a second propulsor blade row connected to said second drive shaft; and a booster compressor including a first compressor blade row connected to said first drive shaft and a second compressor blade row connected to said second drive shaft.
2. A gas turbine engine comprising: a gas generator effective for generating combustion gases; a power turbine including first and second counterrotatable turbine blade rows effective for rotating first and second drive shafts, respectively; a fan section including a first fan blade row connected to said first drive shaft and a second fan blade row connected to said second drive shaft; and a booster compressor including a first compressor blade row connected to said first drive shaft and a second compressor blade row connected to said second drive shaft.
3. A gas turbine engine comprising: a gas generator effective for generating combustion gases; a power turbine including a first rotor having a plurality of first turbine blade rows extending radially inwardly therefrom and a second rotor having a plurality of second turbine blade rows extending radially outwardly therefrom, said first and second turbine rotors being counterrotatable and effective for driving first and second drive shafts, respectively; a propulsor section including a first propulsor blade row connected to said first drive shaft and a second propulsor blade row connected to said second drive shaft; and a booster compressor including a first compressor blade row connected to said first drive shaft and a second compressor blade row connected to said second drive shaft.
4. A gas turbine engine comprising: a gas generator effective for generating combustion gases; a power turbine including a first rotor having a plurality of first turbine blade rows extending radially inwardly therefrom and a second rotor having a plurality of second turbine blade rows extending radially outwardly therefrom, said first and second turbine rotors being counterrotatable and effective for driving first and second drive shafts, respectively; a fan section including a first fan blade row connected to said first drive shaft and a second fan blade row connected to said second drive shaft; and a booster compressor including a first compressor blade row connected to said first drive shaft and a second compressor blade row connected to said second drive shaft.
5. A gas turbine engine comprising: a gas generator effective for generating combustion gases; a power turbine including a first rotor having a plurality of first turbine blade rows extending radially inwardly therefrom and a second turbine rotor having a plurality of second turbine blade rows extending radially outwardly therefrom, said first and second turbine rotors being counterrotatable and effective for driving first and second drive shafts, respectively; a fan section including a first fan blade row connected to said first drive shaft and a second fan blade row connected to said second drive shaft; and a compressor including a first compressor rotor connected to said first drive shaft having a plurality or first compressor blade rows extending radially outwardly therefrom, and a second compressor rotor connected to said second drive shaft having a plurality of second compressor blade rows extending radially inwardly therefrom.
6. A gas turbine engine, as recited in claim 5, wherein said second fan blade row is located axially aft of said first fan blade row, said fan section being effective to produce a fan flow.
7. A gas turbine engine, as recited in claim 6, further comprising: blade pitch actuation means for varying the pitch of said second fan blade row, said means being effective to reverse said fan flow.
8. A gas turbine engine substantially as hereinbefore described with reference to and as illustrated in Figures 1, 3 and 4, Figure 2 or Figure 6 of the drawings.
GB08505193A 1984-03-02 1985-02-28 High bypass ratio counter-rotating turbofan engine Withdrawn GB2155110A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US58568784A 1984-03-02 1984-03-02

Publications (2)

Publication Number Publication Date
GB8505193D0 GB8505193D0 (en) 1985-04-03
GB2155110A true GB2155110A (en) 1985-09-18

Family

ID=24342533

Family Applications (1)

Application Number Title Priority Date Filing Date
GB08505193A Withdrawn GB2155110A (en) 1984-03-02 1985-02-28 High bypass ratio counter-rotating turbofan engine

Country Status (5)

Country Link
JP (1) JPS60256521A (en)
DE (1) DE3507035A1 (en)
FR (1) FR2560642A1 (en)
GB (1) GB2155110A (en)
IT (1) IT1183455B (en)

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2174762A (en) * 1985-05-01 1986-11-12 Gen Electric Counter rotation power turbine
GB2194292A (en) * 1986-08-29 1988-03-02 Gen Electric High bypass ratio counterrotating turbofan engine
FR2603343A1 (en) * 1986-08-29 1988-03-04 Gen Electric ANALYTICAL BLOWER REACTOR WITHOUT HIGH-DILUTION CONTRAROTATIVE GEARBOX
FR2605679A1 (en) * 1986-10-24 1988-04-29 Culica Georges Francois Multi-spool multi-bypass turbo jet engine with a drum rotor
US4751816A (en) * 1986-10-08 1988-06-21 Rolls-Royce Plc Turbofan gas turbine engine
GB2199375A (en) * 1986-12-23 1988-07-06 Rolls Royce Plc A turbofan gas turbine engine
FR2615906A1 (en) * 1987-05-27 1988-12-02 Mtu Muenchen Gmbh REACTOR COMBINED, SWITCHABLE, FOR THE TRAINING OF AIRCRAFT AND SPECIAL EQUIPMENT
GB2207191A (en) * 1987-07-06 1989-01-25 Gen Electric Gas turbine engine
GB2218741A (en) * 1988-05-09 1989-11-22 Gen Electric Gas turbine engine with counter-rotating twin fan section
DE3905282C1 (en) * 1987-10-13 1990-05-31 Karl Dipl.-Ing. 2742 Gnarrenburg De Kastens Propeller fan
GB2196390B (en) * 1986-10-16 1991-06-26 Rolls Royce Plc Intake for turbopropeller gas turbine engine.
EP1387060A2 (en) * 2002-07-30 2004-02-04 General Electric Company Aircraft gas turbine engine with control vanes for counter rotating low pressure turbines
EP1394385A1 (en) * 2002-08-19 2004-03-03 General Electric Company Aircraft gas turbine engine with tandem non-interdigitated counter rotating low pressure turbines
GB2408072A (en) * 2003-11-15 2005-05-18 Rolls Royce Plc Contra rotatable turbine system
FR2866387A1 (en) * 2004-02-12 2005-08-19 Snecma Moteurs Jet engine, has low pressure compressor that is disposed axially between blades of front fan and that of aft fan, and stator with variable setting that is placed downstream of outer grid
DE19828562B4 (en) * 1998-06-26 2005-09-08 Mtu Aero Engines Gmbh Engine with counter-rotating rotors
EP2101040A2 (en) 2008-03-11 2009-09-16 Rolls-Royce Deutschland Ltd & Co KG Turbomachine with multi-flow rotor assembly
WO2010136684A1 (en) 2009-05-29 2010-12-02 Snecma Stationary actuator device for controlling the orientation of the blades of a turboprop fan
WO2010136685A2 (en) 2009-05-29 2010-12-02 Snecma Movable actuator device for controlling the orientation of the blades of a turboprop fan
FR2946012A1 (en) * 2009-05-29 2010-12-03 Snecma DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A TURBOPROPULSEUR
US10677158B2 (en) 2015-12-29 2020-06-09 General Electric Company Method and system for in-line distributed propulsion
WO2020221548A1 (en) * 2019-04-30 2020-11-05 Safran Aircraft Engines Improved architecture of a turbomachne with counter-rotating turbine
RU2802490C2 (en) * 2019-04-30 2023-08-29 Сафран Эркрафт Энджинз Improved design of gas turbine engine with bi-rotative turbine with opposite rotation of shafts

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2606081A1 (en) * 1986-10-29 1988-05-06 Snecma PROPULSION ENGINE WITH CONTRAROTATING WORKING TURBINES
DE3734624A1 (en) * 1987-10-13 1989-05-03 Kastens Karl Propeller fan
DE3834511A1 (en) * 1987-10-13 1990-04-12 Kastens Karl Propeller fan
FR2646473B1 (en) * 1989-04-26 1991-07-05 Snecma MOTOR WITH CONTRAROTATIVE TRACTOR BLOWERS
JPH03217625A (en) * 1990-01-22 1991-09-25 Hiroyasu Tanigawa All moving blade gas turbine
DE4012103C1 (en) * 1990-04-14 1991-07-25 Karl Dipl.-Ing. 2742 Gnarrenburg De Kastens Hypersonic aircraft reaction drive - has flow tube with frontal air entry slot and trough at trailing end
DE102004040275B4 (en) * 2004-08-19 2007-11-08 Kevork Nercessian Turbine engine
DE102018109357B4 (en) * 2018-04-19 2023-12-21 Arianegroup Gmbh Method for operating an aircraft with at least one engine comprising a turbomachine

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB582620A (en) * 1942-04-29 1946-11-22 Karl Baumann Improvements in and relating to power plant comprising elastic fluid turbines driving load shafts through speed reduction transmission gearing
GB586570A (en) * 1943-03-18 1947-03-24 Karl Baumann Improvements in internal combustion turbine plant for propulsion

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB582620A (en) * 1942-04-29 1946-11-22 Karl Baumann Improvements in and relating to power plant comprising elastic fluid turbines driving load shafts through speed reduction transmission gearing
GB586570A (en) * 1943-03-18 1947-03-24 Karl Baumann Improvements in internal combustion turbine plant for propulsion

Cited By (55)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2174762A (en) * 1985-05-01 1986-11-12 Gen Electric Counter rotation power turbine
GB2174762B (en) * 1985-05-01 1990-04-04 Gen Electric Counter rotation power turbine
GB2194292A (en) * 1986-08-29 1988-03-02 Gen Electric High bypass ratio counterrotating turbofan engine
FR2603343A1 (en) * 1986-08-29 1988-03-04 Gen Electric ANALYTICAL BLOWER REACTOR WITHOUT HIGH-DILUTION CONTRAROTATIVE GEARBOX
FR2603344A1 (en) * 1986-08-29 1988-03-04 Gen Electric HIGH DILUTION RATE CONTRAROTATIVE DOUBLE-FLOW TURBOREACTOR
GB2194593A (en) * 1986-08-29 1988-03-09 Gen Electric High bypass ratio, counter rotating gearless front fan engine
GB2194593B (en) * 1986-08-29 1991-05-15 Gen Electric High bypass ratio, counter rotating gearless front fan engine
US4751816A (en) * 1986-10-08 1988-06-21 Rolls-Royce Plc Turbofan gas turbine engine
GB2196390B (en) * 1986-10-16 1991-06-26 Rolls Royce Plc Intake for turbopropeller gas turbine engine.
FR2605679A1 (en) * 1986-10-24 1988-04-29 Culica Georges Francois Multi-spool multi-bypass turbo jet engine with a drum rotor
GB2199375A (en) * 1986-12-23 1988-07-06 Rolls Royce Plc A turbofan gas turbine engine
GB2199375B (en) * 1986-12-23 1991-05-08 Rolls Royce Plc A turbofan gas turbine engine.
US4827712A (en) * 1986-12-23 1989-05-09 Rolls-Royce Plc Turbofan gas turbine engine
US4909031A (en) * 1987-05-27 1990-03-20 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Combined multi-speed jet engine for the drive of airplanes and space vehicles
GB2205360A (en) * 1987-05-27 1988-12-07 Mtu Muenchen Gmbh Composite fanjet/ramjet propulsion device
FR2615906A1 (en) * 1987-05-27 1988-12-02 Mtu Muenchen Gmbh REACTOR COMBINED, SWITCHABLE, FOR THE TRAINING OF AIRCRAFT AND SPECIAL EQUIPMENT
GB2205360B (en) * 1987-05-27 1992-01-22 Mtu Muenchen Gmbh Composite changeover-type reaction power unit for aircraft
US4809498A (en) * 1987-07-06 1989-03-07 General Electric Company Gas turbine engine
GB2207191A (en) * 1987-07-06 1989-01-25 Gen Electric Gas turbine engine
GB2207191B (en) * 1987-07-06 1992-03-04 Gen Electric Gas turbine engine
DE3905282C1 (en) * 1987-10-13 1990-05-31 Karl Dipl.-Ing. 2742 Gnarrenburg De Kastens Propeller fan
GB2218741B (en) * 1988-05-09 1993-01-06 Gen Electric Gas turbine engine
GB2218741A (en) * 1988-05-09 1989-11-22 Gen Electric Gas turbine engine with counter-rotating twin fan section
DE19828562B4 (en) * 1998-06-26 2005-09-08 Mtu Aero Engines Gmbh Engine with counter-rotating rotors
EP1387060A2 (en) * 2002-07-30 2004-02-04 General Electric Company Aircraft gas turbine engine with control vanes for counter rotating low pressure turbines
EP1387060A3 (en) * 2002-07-30 2005-10-12 General Electric Company Aircraft gas turbine engine with control vanes for counter rotating low pressure turbines
EP1394385A1 (en) * 2002-08-19 2004-03-03 General Electric Company Aircraft gas turbine engine with tandem non-interdigitated counter rotating low pressure turbines
GB2408072A (en) * 2003-11-15 2005-05-18 Rolls Royce Plc Contra rotatable turbine system
FR2866387A1 (en) * 2004-02-12 2005-08-19 Snecma Moteurs Jet engine, has low pressure compressor that is disposed axially between blades of front fan and that of aft fan, and stator with variable setting that is placed downstream of outer grid
EP1566522A1 (en) * 2004-02-12 2005-08-24 Snecma Moteurs Double fan turbofan engine having variable fan guide vanes
US7299621B2 (en) 2004-02-12 2007-11-27 Snecma Moteurs Three-spool by-pass turbojet with a high by-pass ratio
CN1654804B (en) * 2004-02-12 2011-06-01 斯奈克玛公司 Three-axis bypass turbojet engine having bypass ratio
EP2101040A2 (en) 2008-03-11 2009-09-16 Rolls-Royce Deutschland Ltd & Co KG Turbomachine with multi-flow rotor assembly
EP2101040A3 (en) * 2008-03-11 2012-07-25 Rolls-Royce Deutschland Ltd & Co KG Turbomachine with multi-flow rotor assembly
FR2946012A1 (en) * 2009-05-29 2010-12-03 Snecma DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A TURBOPROPULSEUR
RU2525101C2 (en) * 2009-05-29 2014-08-10 Снекма Device for turboprop fan blade orientation control
FR2946010A1 (en) * 2009-05-29 2010-12-03 Snecma FIXED CYLINDER DEVICE FOR CONTROLLING BLOWER BLADES OF A TURBOPROPULSER
WO2010136685A3 (en) * 2009-05-29 2011-01-20 Snecma Movable actuator device for controlling the orientation of the blades of a turboprop fan
WO2010136686A3 (en) * 2009-05-29 2011-01-20 Snecma Device for controlling the orientation of the blades of a turboprop fan
WO2010136685A2 (en) 2009-05-29 2010-12-02 Snecma Movable actuator device for controlling the orientation of the blades of a turboprop fan
CN102448819A (en) * 2009-05-29 2012-05-09 斯奈克玛 Movable actuator device for controlling the orientation of the blades of a turboprop fan
WO2010136684A1 (en) 2009-05-29 2010-12-02 Snecma Stationary actuator device for controlling the orientation of the blades of a turboprop fan
CN102448819B (en) * 2009-05-29 2014-07-09 斯奈克玛 Movable actuator device for controlling the orientation of the blades of a turboprop fan
RU2523515C2 (en) * 2009-05-29 2014-07-20 Снекма Device for moving power cylinder for control over turboprop fan vanes
RU2522752C2 (en) * 2009-05-29 2014-07-20 Снекма Stationary device of turboprop fan vane pitch controller actuator
FR2946011A1 (en) * 2009-05-29 2010-12-03 Snecma MOBILE ROLLER DEVICE FOR CONTROLLING THE ORIENTATION OF BLOWER BLADES OF A TURBOPROPULSOR
US8985954B2 (en) 2009-05-29 2015-03-24 Snecma Device for controlling the pitch of fan blades of a turboprop
US9085979B2 (en) 2009-05-29 2015-07-21 Snecma Movable actuator device for controlling the pitch of fan blades of a turboprop
US9284041B2 (en) 2009-05-29 2016-03-15 Snecma Stationary actuator device for controlling the pitch of fan blades of a turboprop
US10677158B2 (en) 2015-12-29 2020-06-09 General Electric Company Method and system for in-line distributed propulsion
WO2020221548A1 (en) * 2019-04-30 2020-11-05 Safran Aircraft Engines Improved architecture of a turbomachne with counter-rotating turbine
FR3095670A1 (en) * 2019-04-30 2020-11-06 Safran Aircraft Engines Improved architecture of a contra-rotating turbine engine
RU2802490C2 (en) * 2019-04-30 2023-08-29 Сафран Эркрафт Энджинз Improved design of gas turbine engine with bi-rotative turbine with opposite rotation of shafts
US12092020B2 (en) 2019-04-30 2024-09-17 Safran Aircraft Engines Architecture of a turbomachine with counter-rotating turbine
RU2816769C1 (en) * 2022-11-07 2024-04-05 Юрий Николаевич Михайлов Propfan aircraft gas turbine engine

Also Published As

Publication number Publication date
JPS60256521A (en) 1985-12-18
GB8505193D0 (en) 1985-04-03
FR2560642A1 (en) 1985-09-06
IT1183455B (en) 1987-10-22
DE3507035A1 (en) 1985-09-12
IT8519739A0 (en) 1985-03-01

Similar Documents

Publication Publication Date Title
GB2155110A (en) High bypass ratio counter-rotating turbofan engine
US4790133A (en) High bypass ratio counterrotating turbofan engine
US4860537A (en) High bypass ratio counterrotating gearless front fan engine
CA1233325A (en) Counter rotation power turbine
US5079916A (en) Counter rotation power turbine
EP1403499B1 (en) Counter rotating fan aircraft gas turbine engine with aft booster
EP1403500B1 (en) Aircraft gas turbine engine having variable torque split counter rotating low pressure turbines and single direction of rotation booster aft of counter rotating fans
US4251987A (en) Differential geared engine
EP2472066B1 (en) Variable geometry vane system for a gas turbine engine and corresponding gas turbine engine
CA1262409A (en) Counter rotation power turbine
US4968217A (en) Variable pitch arrangement for a gas turbine engine
CN113217582B (en) Gear box for engine
EP0203881A1 (en) Ducted prop engine
GB2218741A (en) Gas turbine engine with counter-rotating twin fan section
JPS61155603A (en) Gas turbine engine
US5105618A (en) Counterrotating fan engine
US4767271A (en) Gas turbine engine power turbine
JPH0142879B2 (en)
US5103635A (en) Contra-rotating fan engine
GB2189844A (en) Gas turbine engines
JP2927790B2 (en) Gas turbine engine
US11753939B2 (en) Turbomachine with alternatingly spaced rotor blades
US2504414A (en) Gas turbine propulsion unit
US3462953A (en) Gas turbine jet propulsion engine
JPS63106335A (en) Gas turbine engine

Legal Events

Date Code Title Description
WAP Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1)