GB2169968A - Turbo-propeller aircraft gas turbine engines - Google Patents

Turbo-propeller aircraft gas turbine engines Download PDF

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Publication number
GB2169968A
GB2169968A GB8501555A GB8501555A GB2169968A GB 2169968 A GB2169968 A GB 2169968A GB 8501555 A GB8501555 A GB 8501555A GB 8501555 A GB8501555 A GB 8501555A GB 2169968 A GB2169968 A GB 2169968A
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GB
United Kingdom
Prior art keywords
propeller
engine
turbo
turbine
aircraft gas
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Withdrawn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
GB8501555A
Inventor
Maurice Ian Taylor
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB8501555A priority Critical patent/GB2169968A/en
Priority to DE19863600852 priority patent/DE3600852A1/en
Priority to JP780386A priority patent/JPS61197724A/en
Priority to FR8600792A priority patent/FR2576359A1/en
Publication of GB2169968A publication Critical patent/GB2169968A/en
Withdrawn legal-status Critical Current

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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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/20—Adaptations of gas-turbine plants for driving vehicles
    • F02C6/206—Adaptations of gas-turbine plants for driving vehicles the vehicles being airscrew driven
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • 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
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/325—Application in turbines in gas turbines to drive unshrouded, high solidity propeller

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Separation By Low-Temperature Treatments (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)

Abstract

The present invention provides a turbo-propeller aircraft gas turbine engine of the pusher type which reduces the production of wakes and disturbances in the airflow passing over an engine pod to the propeller(s). The engine pod (12) encloses the compressors (20,22), combustor (24) and turbines (26,28). A propeller (50) is positioned downstream of the engine and is driven by turbine (28) via a reduction gearbox (36). The reduction gearbox (36) is positioned axially between the turbine (28) and the propeller (50). An accessory wheelcase (34) for driving engine accessories, eg. fuel pumps, oil pumps, is positioned within a nose bullet (14) upstream of the compressor (20) and is driven by turbine (28). The reduction gearbox (36) and accessory wheelcase (34) are so positioned to produce an axisymmetric aerodynamically shaped engine pod (12) upstream of the propeller (50) to effect reduction of wakes and disturbances in the airflow passing to the propeller (50). <IMAGE>

Description

SPECIFICATION Turbo-propeller aircraft gas turbine engines The present invention relates to aircraft gas turbine engines of the turbo-propeller type, commonly known as turbo-props.
These engines usually have an engine pod one or more compressors, a combustion system, compressor driving turbines, and one or more propellers driven by a turbine via reduction gearing. The propeller or propellers may be driven from a low pressure turbine or a free power turbine positioned downstream of the low pressure turbine. These engines also have an accessory wheel case which is driven by a turbine so as to provide drive for fuel pumps, lubricant and other engine accessories.
Turbo-props of the type with the propeller or propellers positioned at the downstream end of the gas turbine engine are generally known as pusher turbo-props. Pusher turbo-props may suffer from a problem in that as the air flows over the engine pod upstream of the propeller or propellers wakes or disturbances are introduced into the air flow due to the shape of the engine pod and this reduces the efficiency of the propeller or propellers.
The present invention seeks to provide a turbopropeller aircraft gas turbine engine of the pusher type which reduces the production of wakes and disturbances in the air flow passing over the engine pod to the propeller or propellers.
Accordingly the present invention provides a turbo-propeller aircraft gas turbine engine of the pusher type comprising in flow series compressor means, combustion means, a compressor driving turbine means, a propeller driving turbine means, at least one propeller being driven by the propeller driving turbine means via a reduction gearbox, the engine upstream of the at least one propeller being enclosed in an engine pod, a nose bullet being positioned upstream of the compressor means and defining an annular inlet with the upstream end of the engine pod, the reduction gearbox being positioned downstream of the propeller driving turbine means and upstream of the at least one propeller, the compressor means, the compressor driving turbine means, the propeller driving turbine means, the reduction gearbox and the at least one propeller being coaxial, and an accessory wheelcase being positioned within the nose bullet upstream of the compressor means and being driven by a turbine means, the reduction gearbox and accessory wheelcase being so positioned to produce an axisynmetric aerodynamically shaped engine pod upstream of the at least one propeller to reduce the production of wakes and disturbances in the airflow passing over the engine pod to the at least one propeller.
The compressor means may comprise a low pressure compressor and a high pressure compressor, and the compressor driving turbine means comprises a low pressure turbine driving the low pressure compressor and high pressure turbine driving the high pressure compressor.
The propeller driving turbine means may be the low pressure turbine or a power turbine positioned downstream of and driven by exhaust gases from the low pressure turbine.
The accessory wheelcase may be driven by the low pressure turbine, the high pressure turbine or a power turbine.
The engine pod may have an annular exhaust upstream of the at least one propeller.
The engine pod may have a radially extending strut upstream of the at least one propeller, the strut having an internal exhaust duct and the exhaust duct having one or more exits in the strut for directing exhaust gases in a downstream direction over the surface of the strut.
The at least one propeller has a propeller spinner, the propeller spinner having an axially extending internal duct to convey the exhaust gases to an annular exit downstream of the at least one propeller.
The reduction gearbox may be an epicyclic reduction gearbox.
The engine may have a pair of contra-rotating propellers. The propeller or propellers may be of the propfan type.
The present invention will be more fully described by way of reference to the accompanying drawings in which: Figure 1 shows a cut-away view of a turbo-propeller aircraft gas turbine engine of the pusher type according to the present invention.
Figure 2 shows a cut-away view of an alternative embodiment of a turbo-propeller aircraft gas turbine engine of the pusher type according to the present invention.
Figure 3 shows a cut-away view of a third embodiment of a turbo-propeller aircraft gas turbine engine of the pusher type according to the present invention.
Figure 4 shows a cut-away view of a fourth embodiment of a turbo-propeller aircraft gas turbine engine of the pusher type according to the present invention.
Figure 5 shows an enlarged view of part of an engine pod and propeller spinner sealing arrangement in figure 4.
and Figure 6 shows a cut-away view of a further embodiment of a turbo-propeller aircraft gas turbine engine of the pusher type according to the present invention.
Referring to Figure 1, a turbo-propeller aircraft gas turbine engine 10 of the pusher type comprises a gas generator 11 which comprises in flow series a low pressure compressor 20, a high pressure compressor 22, a combustion system 24, a high pressure turbine 26, a low pressure turbine 28 and an annular exhaust 18. The gas generator 11 is enclosed by an engine pod 12 and a nose bullet 14 is positioned upstream of the low pressure compressor 20 and forms an annular inlet 16 with the upstream end of the engine pod 16. The low and high pressure compressors 20 and 22 respectively compress air entering the gas turbine engine 10 through the inlet 16. The compressed air is then supplied into the combustor 24 where fuel is burnt to produce hot gases.The hot gases flow through and drive the high and low pressure turbines 26 and 28 respectively, which in turn drive the high and low pressure compressors 22 and 20 respectively via coaxial shafts 30 and 32 respectively.
A multi-bladed propeller 50 is positioned downstream of, and coaxially with the gas generator 11, and the propeller 50 is provided with an aerodynamically shaped propeller spinner 52. The multibladed propeller 50 is driven by a turbine via a reduction gearbox 36, in this embodiment the low pressure turbine 28 drives the propeller. The reduction gearbox 36 is positioned coaxially with the propeller 50 and gas generator 11, and axially between the low pressure turbine 28 and the propeller 50.
An accessory wheelcase 34 is provided for driving engine accessories, for example, fuel pumps oil pumps, etc, and the accessory wheelcase 34 is positioned upstream of the low pressure compressor 20 within the nose bullet 14. The accessory wheelcase 34 is driven by a turbine, in this embodiment the low pressure turbine 28 via the shaft 32.
By positioning the reduction gearbox 36 coaxially with the gas generator 11 and the propeller 50, and axially between the low pressure turbine 28 and the propeller 50, and by positioning the accessory wheelcase 34 upstream of the low pressure compressor 20 within the nose bullet 14, the engine pod 12 can be made a relatively small diameter, axisymmetric and aerodynamically shaped upstream of the propeller 50 so as to reduce wakes and disturbances in the air flow passing over the engine pod 12 to the propeller 50. Reduction of wakes and disturbances in the air flow passing to the propeller 50 increases the efficiency of the propeller 50.
Prior art turbo-propeller aircraft gas turbine engines have suffered from the production of wakes and disturbances in the air flow passing over the engine pod to the propeller. These wakes and disturbances have reduced the efficiency of the propeller and have been caused because the engine pod is not synmetric and not aerodynamic. The main causes of this has generally been that the accessory wheelcase has been positioned on the outside of the compressor casing and has been driven by a radially extending shaft from a main drive shaft.
Figure 2 shows a turbo-propeller aircraft gas turbine engine 10 of the pusher type similar to that in figure 1. The gas generator 11 is identical to that in figure 1 and like parts are denoted by like numerals. A multi-bladed propeller 50 is positioned downstream of, and coaxially with the gas generator 11, and the propeller 50 is provided with an aerodynamically shaped propeller spinner 52. The multi-bladed propeller 50 is driven by a power turbine 40 via a shaft 42 and a reduction gearbox 36.
The power turbine 40 is positioned downstream of the low pressure turbine 28, and the exhaust gases from the gas generator 11 drive the power turbine 40. The reduction gearbox 36, shaft 42, power turbine 40 and propeller 50 are coaxial with the gas generator 11. The reduction gearbox 36 is positioned axially between the low pressure turbine 28 and the propeller 50.
The accessory wheelcase 34 is positioned upstream of the low pressure compressor 20 within the nose bullet 14, and is driven by the low pressure turbine 28 via shaft 32.
The engine pod 12 is again of relatively small diameter, axisymmetric and aerodynamically shaped upstream of the propeller 50 so as to reduce wakes and disturbances in the airflow passing over the engine pod 12 to the propeller 50.
Figure 3 shows a turbo-propeller aircraft gas turbine engine 10 of the pusher type similar to that in figure 1. The gas generator 11 is identical to that in figure 1 and like parts are denoted by like numerals. A pair of contra-rotating multi-bladed propellers 70, 72 of the propfan type, ie., of thin section and highly swept to delay shock wave formation and having the ability to operate at a high power loading, are positioned downstream of, and coaxially with the gas generator 11, and the propellers 70, 72 are provided with aerodynamically shaped spinners 74, 76 respectively. The contra-rotating propellers 70, 72 are driven by the low pressure turbine 28 via the reduction gearbox 36. The reduction gearbox 36 is positioned coaxially with the propellers 70, 72 and gas generator 11, and axially between the low pressure turbine 28 and the propellers 70, 72.
The accessory wheelcase 34 is positioned upstream of the low pressure compressor 20 within the nose bullet 14, and is driven by the low pressure turbine 28 via shaft 32.
The engine pod 12 is of relatively small diameter, axisymmetric and aerodynamically shaped upstream of the contra-rotating propellers 70, 72 so as to reduce wakes and disturbances in the airflow passing over the engine pod 12 to the propellers 70, 72.
In this embodiment the gas generator 11 does not have an annular exhaust 18, but has a strut 60 positioned upstream of the propellers 70, 72 and downstream of the low pressure turbine 28, and which extends radially from the engine pod 12 and may form part of a structure to carry the engine from an aircraft. The strut 60 has an internal duct 62 through which the exhaust gases from the gas generator 11 flow. The exhaust gases flow to a nozzle 64 which may be used to direct the exhaust gases in a downstream direction over the tail of the aircraft, as described more fully in our copending published application GB 2138507A. The strut 60 may be provided with exits 66, generally slots with vanes, to discharge the exhaust gases in a downstream direction over the strut to suppress wakes produced by the strut 60.
The engine pod 12 is of relatively small diameter, axisymmetric, and aerodynamically shaped upstream of the contra-rotating propellers 70, 72 so as to reduce wakes and disturbances in the airflow passing over the engine pod 12 to the propellers.
Figure 4 shows a turbo-propeller aircraft gas turbine engine 10 of the pusher type similar to that in figure 1. The gas generator 11 is identical to that in figure 1 and like parts are denoted by like numerals. The propeller 80 is positioned downstream of, and coaxially with the gas generator 11, and the propeller 80 is provided with an aerodynamic spinner 82. The propeller 80 is driven by the low pressure turbine 28 via a reduction gearbox 36 positioned coaxially with the propeller 80 and gas generator 11, and axially between the low pressure turbine 28 and the propeller 80. The accessory wheelcase 34 is positioned upstream of the low pressure compressor 20 within the nose bullet 14, and is driven by the low pressure turbine 28.
The spinner 82 is provided with an internal annular duct 88 which extends axially and conveys the exhaust gases from the gas generator 11 between the blade roots 90 of the propeller 80 to an annular exit 86 in the spinner 82 downstream of the propeller 80. The annular duct 88 thus directs the exhaust gases away from the propeller blades.
A seal 84 is provided between the upstream end of the spinner 82 and the downstream end of the engine pod 12, and is shown to an enlarged scale in figure 5. The upstream end 94 of the spinner 82 extends axially beyond the downstream end 92 of the engine pod 12 and is spaced radially therefrom. A number of annular ribs 96 extend radially from the upstream end 94 of the spinner 82 towards the downstream end 92 of the engine pod 12, or visa-versa, to form a labyrinth type seal.
Figure 6 shows a turbo-propeller aircraft gas turbine engine 10 of the pusher type similar to that in figure 4. The gas generator is identical to that in figure 4 and like parts are denoted by like numerals. The propeller 80 is positioned downstream of, and coaxially with the gas generator 11, and the propeller 80 is provided with a spinner 82. The propeller 80 is driven by a power turbine 40 via a shaft 42 and a reduction gearbox 36. The power turbine 40 is positioned downstream of the low pressure turbine 28. The power turbine 40, shaft 42 and reduction gearbox 36 are coaxial with the gas generator 11 and propeller 80. The accessory wheelcase 34 is again positioned upstream of the low pressure compressor 20 within the nose bullet 14, and is driven by the power turbine 40 via a shaft 44 which is coaxial with shafts 30, 32, 42.
The reduction gearbox in the examples may be an epicyclic reduction gearbox.

Claims (14)

1. A turbo-propeller aircraft gas turbine engine of the pusher type comprising in flow series compressor means, combustion means, a compressor driving turbine means, a propeller driving turbine means, at least one propeller being driven by the propeller driving turbine means via a reduction gearbox, the engine upstream of the at least one propeller being enclosed in an engine pod, a nose bullet being positioned upstream of the compressor means, and defining an annular inlet with the upstream end of the engine pod, the reduction gearbox being positioned downstream of the propeller driving turbine means and upstream of the at least one propeller, the compressor means, the compressor driving turbine means, the propeller driving turbine means, the reduction gearbox and the at least one propeller being coaxial, and an accessory wheelcase being positioned within the nose bullet upstream of the compressor means and being driven by a turbine means, the reduction gearbox and accessory wheelcase being so positioned to produce an axisymmetric aerodynamically shaped engine pod upstream of the at least one propeller to reduce the production of wakes and disturbances in the airflow passing over the engine pod to the at least one propeller.
2. A turbo-propeller aircraft gas turbine engine of the pusher type as claimed in claim 1 in which the compressor means comprises a low pressure compressor and a high pressure compressor and the compressor driving turbine means comprises a low pressure turbine driving the low pressure compressor and a high pressure turbine driving the high pressure compressor.
3. A turbo-propeller aircraft gas turbine engine of the pusher type as claimed in claim 2 in which the propeller driving turbine means is the low pressure turbine.
4. A turbo-propeller aircraft gas turbine engine of the pusher type as claimed in claim 2 in which the propeller driving turbine means comprises a power turbine positioned downstream of and driven by exhaust gases from the low pressure turbine.
5. A turbo-propeller aircraft gas turbine engine of the pusher type as claimed in claim 2, claim 3 or claim 4 in which the accessory wheelcase is driven by the low pressure turbine.
6. A turbo-propeller aircraft gas turbine engine of the pusher type as claimed in claim 4 in which the accessory wheelcase is driven by the power turbine.
7. A turbo-propeller aircraft gas turbine engine of the pusher type as claimed in claim 2, claim 3 or claim 4 in which the accessory wheelcase is driven by the high pressure turbine.
8. A turbo-propeller aircraft gas turbine engine of the pusher type as claimed in any of claims 1 to 7 in which the engine pod has an annular exhaust upstream of the at least one propeller.
9. A turbo-propeller aircraft gas turbine engine of the pusher type as claimed in any of claims 1 to 7 in which the engine pod has a radially extending strut upstream of the at least one propeller, the strut having an internal exhaust duct and the exhaust duct having one or more exits in the strut for directing exhaust gases in a downstream direction over the surface of the strut.
10. A turbo-propeller aircraft gas turbine engine of the pusher type as claimed in any of claims 1 to 7 in which the at least one propeller has a propeller spinner, the propeller spinner having an axially extending internal duct to convey the exhaust gases to an annular exit downstream of the at least one propeller.
11. A turbo-propeller aircraft gas turbine engine of the pusher type as claimed in any of claims 1 to 10 in which the reduction gearbox is an epicyclic reduction gearbox.
12. A turbo-propeller aircraft gas turbine engine of the pusher type as claimed in any of claims 1 to 11 in which the engine has a pair of contra-rotating propellers.
13. A turbo-propeller aircraft gas turbine engine of the pusher type as claimed in any of claims 1 to 12 in which the propeller or propellers are of the propfan type.
14. A turbo-propeller aircraft gas turbine engine of the pusher type substantially as herein described with reference to and as illustrated in figure 1, 2, 3,4 or 6
GB8501555A 1985-01-22 1985-01-22 Turbo-propeller aircraft gas turbine engines Withdrawn GB2169968A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB8501555A GB2169968A (en) 1985-01-22 1985-01-22 Turbo-propeller aircraft gas turbine engines
DE19863600852 DE3600852A1 (en) 1985-01-22 1986-01-14 TURBO PROPELLER GAS TURBINE PLANE ENGINE
JP780386A JPS61197724A (en) 1985-01-22 1986-01-17 Gas turbine engine for turbo propella airplane
FR8600792A FR2576359A1 (en) 1985-01-22 1986-01-21 GAS TURBINE ENGINE WITH TURBOPROPULSER FOR AIRCRAFT

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB8501555A GB2169968A (en) 1985-01-22 1985-01-22 Turbo-propeller aircraft gas turbine engines

Publications (1)

Publication Number Publication Date
GB2169968A true GB2169968A (en) 1986-07-23

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Family Applications (1)

Application Number Title Priority Date Filing Date
GB8501555A Withdrawn GB2169968A (en) 1985-01-22 1985-01-22 Turbo-propeller aircraft gas turbine engines

Country Status (4)

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JP (1) JPS61197724A (en)
DE (1) DE3600852A1 (en)
FR (1) FR2576359A1 (en)
GB (1) GB2169968A (en)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4964844A (en) * 1987-09-05 1990-10-23 Rolls-Royce Plc Gearbox arrangement for driving coaxial contra rotating multi-bladed rotors
WO1993006007A1 (en) * 1991-09-17 1993-04-01 Rolls-Royce Plc Ducted fan gas turbine engine accessory drive system
US5687561A (en) * 1991-09-17 1997-11-18 Rolls-Royce Plc Ducted fan gas turbine engine accessory drive
GB2430013A (en) * 2005-09-09 2007-03-14 Christian Koenig Propeller drive
WO2011033204A1 (en) * 2009-09-18 2011-03-24 Snecma Turbine engine with contra-rotating non-ducted propellers
US8701385B2 (en) 2008-12-05 2014-04-22 Rolls-Royce Deutschland Ltd & Co Kg Method and apparatus for the operation of a turboprop aircraft engine provided with pusher propellers
US8720208B2 (en) 2010-02-26 2014-05-13 Rolls-Royce Deutschland Ltd & Co Kg Aircraft gas turbine engine
WO2014163708A3 (en) * 2013-03-08 2014-12-11 Rolls-Royce Corporation Rotor noise suppression
WO2014195632A1 (en) * 2013-06-06 2014-12-11 Snecma Accessory drive case for a turboprop
CN111706432A (en) * 2020-05-28 2020-09-25 中国航发湖南动力机械研究所 Novel paddle fan engine and propulsion device with same
CN112533826A (en) * 2018-05-17 2021-03-19 杰托普特拉股份有限公司 Combined compressed fluid ejector and propeller propulsion system

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4964844A (en) * 1987-09-05 1990-10-23 Rolls-Royce Plc Gearbox arrangement for driving coaxial contra rotating multi-bladed rotors
WO1993006007A1 (en) * 1991-09-17 1993-04-01 Rolls-Royce Plc Ducted fan gas turbine engine accessory drive system
US5687561A (en) * 1991-09-17 1997-11-18 Rolls-Royce Plc Ducted fan gas turbine engine accessory drive
GB2430013A (en) * 2005-09-09 2007-03-14 Christian Koenig Propeller drive
US7886544B2 (en) * 2005-09-09 2011-02-15 Christian Koenig Propeller or propeller drive
US8701385B2 (en) 2008-12-05 2014-04-22 Rolls-Royce Deutschland Ltd & Co Kg Method and apparatus for the operation of a turboprop aircraft engine provided with pusher propellers
US9017028B2 (en) 2009-09-18 2015-04-28 Snecma Turbine engine with contra-rotating non-ducted propellers
GB2485744A (en) * 2009-09-18 2012-05-23 Snecma Turbine engine with contra-rotating non-ducted propellers
WO2011033204A1 (en) * 2009-09-18 2011-03-24 Snecma Turbine engine with contra-rotating non-ducted propellers
FR2950381A1 (en) * 2009-09-18 2011-03-25 Snecma TURBOMACHINE WITH NON-CARINE CONTRAROTATIVE PROPELLERS
GB2485744B (en) * 2009-09-18 2016-02-24 Snecma A turbine engine having contrarotating unducted propellers
US8720208B2 (en) 2010-02-26 2014-05-13 Rolls-Royce Deutschland Ltd & Co Kg Aircraft gas turbine engine
WO2014163708A3 (en) * 2013-03-08 2014-12-11 Rolls-Royce Corporation Rotor noise suppression
US9650962B2 (en) 2013-03-08 2017-05-16 Rolls-Royce Corporation Rotor noise suppression
WO2014195632A1 (en) * 2013-06-06 2014-12-11 Snecma Accessory drive case for a turboprop
US10145260B2 (en) 2013-06-06 2018-12-04 Safran Aircraft Engines Accessory drive case for a turboprop
CN112533826A (en) * 2018-05-17 2021-03-19 杰托普特拉股份有限公司 Combined compressed fluid ejector and propeller propulsion system
CN111706432A (en) * 2020-05-28 2020-09-25 中国航发湖南动力机械研究所 Novel paddle fan engine and propulsion device with same
CN111706432B (en) * 2020-05-28 2022-03-25 中国航发湖南动力机械研究所 Paddle fan engine and propulsion device with same

Also Published As

Publication number Publication date
DE3600852A1 (en) 1986-07-24
FR2576359A1 (en) 1986-07-25
JPS61197724A (en) 1986-09-02

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