US20100014977A1 - Variable pitch aft propeller vane system - Google Patents
Variable pitch aft propeller vane system Download PDFInfo
- Publication number
- US20100014977A1 US20100014977A1 US12/501,520 US50152009A US2010014977A1 US 20100014977 A1 US20100014977 A1 US 20100014977A1 US 50152009 A US50152009 A US 50152009A US 2010014977 A1 US2010014977 A1 US 2010014977A1
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- United States
- Prior art keywords
- pitch
- propeller
- recited
- vane
- variable pitch
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
- B64C11/48—Units of two or more coaxial propellers
Definitions
- the present disclosure relates to a vane propeller system, and more particularly to a straightened slipstream which recovers swirl energy.
- Turboprop propeller systems that include a single set of blades which rotate in one direction and in one plane of rotation are known as single rotation propellers. Pitch angles ranging from a fully feathered minimum drag angle to pitch angles which provide reverse thrust are typically provided for propeller speed and power management along a propeller axis of rotation. Turboprop propeller systems provide a relatively high level of propeller efficiency. However, a certain significant amount of efficiency may be lost to the swirl energy that the propeller imparts to the slipstream.
- a propulsion system includes a rotationally fixed variable pitch vane system located axially aft of a propeller system.
- a flight control method for an aircraft includes collectively changing a pitch of a rotationally fixed variable pitch vane system located axially aft of a propeller system.
- FIG. 1 is a general perspective partial fragmentary view of an exemplary gas turbine turboprop engine
- FIG. 2 is a schematic block diagram of a rotationally fixed variable pitch vane system.
- FIG. 1 illustrates a general perspective view of a propulsion system 10 that includes a propeller system 20 .
- a propeller system typical of a turboprop aircraft is illustrated in the disclosed embodiment, various rigid prop/rotor systems including tilt rotor and tilt wing systems will also benefit herefrom.
- a gas turbine engine (illustrated schematically at 22 ) which rotates a turbine output shaft 24 at a high speed.
- the turbine output shaft 24 drives a gear reduction gearbox (illustrated schematically at 26 ) which decrease shaft rotation speed and increase output torque.
- the gearbox 26 drives a propeller shaft 28 which rotate a propeller hub 30 and a plurality of propeller blades 32 which extend therefrom about an axis of rotation A.
- Axis A is substantially perpendicular to a plane P which is defined by the propeller blades 32 .
- the plurality of propeller blades 32 are variable pitch in that each propeller blade 32 may be pitched about a pitch axis B defined along the length of the propeller blade 32 .
- Pitch change of the plurality of propeller blades 32 may be accomplished through a pitch change system 34 operated in response to a blade module 36 to change the pitch of each propeller blade 32 .
- the blade module 36 typically includes a processor 36 A, a memory 36 B, and an interface 36 C ( FIG. 2 ).
- the processor 36 A may be any type of known microprocessor having desired performance characteristics.
- the memory 36 B may include various computer readable mediums which store the data and control algorithms described herein.
- the interface 36 C facilitates communication with a higher level control system such as the flight control computer (FCC) 38 as well as other avionics and systems.
- the blade module 36 operates to accomplish speed governing, synchrophasing, beta control, feathering, unfeathering and other collective control of the propeller blades 32 as generally understood.
- a rotationally fixed variable pitch vane system 40 is located aft of the propeller system 20 .
- the vane system 40 includes a multiple of vanes 42 which may be of approximately the same diameter as the propeller blades 32 , however, the number, size, and shape of the vanes 42 may be selected based on a combination of aerodynamic, cost and weight analyses for each specific application.
- the vane system 40 includes a vane pitch change system 44 operated in response to a vane module 46 to change the pitch of each vane 42 .
- the vane pitch change system 44 may be of various forms, but is relatively less complicated than that the propeller system 20 .
- the vane module 46 typically includes a processor 46 A, a memory 46 B, and an interface 46 C ( FIG. 2 ).
- the processor 46 A may be any type of known microprocessor having desired performance characteristics.
- the memory 46 B may include various computer readable mediums which store the data and control algorithms described herein.
- the interface 46 C facilitates communication with a higher level control system such as the flight control computer (FCC) 38 as well as other avionics and systems. It should be understood that the blade module 36 and the vane module 46 may be integrated with each other as well as with the FCC 38 .
- FCC flight control computer
- the pitch angle of the vane system 40 is set by the vane module 46 to straighten the flow, thereby recovering the swirl component from the propeller system 20 .
- the pitch angle of the vane system 40 is set by the vane module 46 to provide the most thrust at a particular operating point, e.g., take off.
- the variable pitch provides maximum propulsive efficiency at each operating point but may result in increased weight, and complexity.
- the pitch angle of the variable pitch vanes 42 may be related as a function of the flight condition to maximize efficiency gains.
- the vanes 42 may be fixed pitch in which the vane pitch angle is fixed for a particular flight condition that provides the most fuel savings which, in one non-limiting embodiment may be a cruise condition.
- the pitch angle of the vane system 40 is set by the vane module 46 to increase propulsive efficiency to provide significant fuel savings; increase thrust at a given condition and power setting to provide improved take-off climb and cruise performance. Alternatively, the same thrust is achieved at a lower power setting which also increases engine life and fuel savings.
- the pitch angle of the vane system 40 is set by the vane module 46 to flat pitch which increases drag, reduces landing distance and reduces aircraft brake wear. That is, the vane system 40 operates as a speed brake in conjunction with, for example, the propeller blade 32 pitch angle set to reverse pitch.
- the pitch angle of the vane system 40 is set by the vane module 46 to a pitch based on an operating point flight condition such as hover flight to increase the efficiency of hover and low speed flight operations.
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Turbines (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
A propulsion system includes a rotationally fixed variable pitch vane system located axially aft of a propeller system.
Description
- The present disclosure claims priority to U.S. Provisional Patent Application Ser. No. 61/134,913, filed Jul. 15, 2008.
- The present disclosure relates to a vane propeller system, and more particularly to a straightened slipstream which recovers swirl energy.
- Turboprop propeller systems that include a single set of blades which rotate in one direction and in one plane of rotation are known as single rotation propellers. Pitch angles ranging from a fully feathered minimum drag angle to pitch angles which provide reverse thrust are typically provided for propeller speed and power management along a propeller axis of rotation. Turboprop propeller systems provide a relatively high level of propeller efficiency. However, a certain significant amount of efficiency may be lost to the swirl energy that the propeller imparts to the slipstream.
- A propulsion system according to an exemplary aspect of the present disclosure includes a rotationally fixed variable pitch vane system located axially aft of a propeller system.
- A flight control method for an aircraft according to an exemplary aspect of the present disclosure includes collectively changing a pitch of a rotationally fixed variable pitch vane system located axially aft of a propeller system.
- Various features will become apparent to those skilled in the art from the following detailed description of the disclosed non-limiting embodiment. The drawings that accompany the detailed description can be briefly described as follows:
-
FIG. 1 is a general perspective partial fragmentary view of an exemplary gas turbine turboprop engine; and -
FIG. 2 is a schematic block diagram of a rotationally fixed variable pitch vane system. -
FIG. 1 illustrates a general perspective view of apropulsion system 10 that includes apropeller system 20. It should be understood that although a propeller system typical of a turboprop aircraft is illustrated in the disclosed embodiment, various rigid prop/rotor systems including tilt rotor and tilt wing systems will also benefit herefrom. - A gas turbine engine (illustrated schematically at 22) which rotates a
turbine output shaft 24 at a high speed. Theturbine output shaft 24 drives a gear reduction gearbox (illustrated schematically at 26) which decrease shaft rotation speed and increase output torque. Thegearbox 26 drives apropeller shaft 28 which rotate apropeller hub 30 and a plurality ofpropeller blades 32 which extend therefrom about an axis of rotation A. Axis A is substantially perpendicular to a plane P which is defined by thepropeller blades 32. - The plurality of
propeller blades 32, in the disclosed, non-limiting embodiment are variable pitch in that eachpropeller blade 32 may be pitched about a pitch axis B defined along the length of thepropeller blade 32. Pitch change of the plurality ofpropeller blades 32 may be accomplished through apitch change system 34 operated in response to ablade module 36 to change the pitch of eachpropeller blade 32. Theblade module 36 typically includes aprocessor 36A, amemory 36B, and aninterface 36C (FIG. 2 ). Theprocessor 36A may be any type of known microprocessor having desired performance characteristics. Thememory 36B may include various computer readable mediums which store the data and control algorithms described herein. Theinterface 36C facilitates communication with a higher level control system such as the flight control computer (FCC) 38 as well as other avionics and systems. Theblade module 36 operates to accomplish speed governing, synchrophasing, beta control, feathering, unfeathering and other collective control of thepropeller blades 32 as generally understood. - A rotationally fixed variable
pitch vane system 40 is located aft of thepropeller system 20. Thevane system 40 includes a multiple ofvanes 42 which may be of approximately the same diameter as thepropeller blades 32, however, the number, size, and shape of thevanes 42 may be selected based on a combination of aerodynamic, cost and weight analyses for each specific application. - The
vane system 40 includes a vanepitch change system 44 operated in response to avane module 46 to change the pitch of eachvane 42. The vanepitch change system 44 may be of various forms, but is relatively less complicated than that thepropeller system 20. - The
vane module 46 typically includes aprocessor 46A, amemory 46B, and aninterface 46C (FIG. 2 ). Theprocessor 46A may be any type of known microprocessor having desired performance characteristics. Thememory 46B may include various computer readable mediums which store the data and control algorithms described herein. Theinterface 46C facilitates communication with a higher level control system such as the flight control computer (FCC) 38 as well as other avionics and systems. It should be understood that theblade module 36 and thevane module 46 may be integrated with each other as well as with the FCC 38. - The pitch angle of the
vane system 40 is set by thevane module 46 to straighten the flow, thereby recovering the swirl component from thepropeller system 20. In additional, the pitch angle of thevane system 40 is set by thevane module 46 to provide the most thrust at a particular operating point, e.g., take off. The variable pitch provides maximum propulsive efficiency at each operating point but may result in increased weight, and complexity. The pitch angle of thevariable pitch vanes 42 may be related as a function of the flight condition to maximize efficiency gains. Alternatively, thevanes 42 may be fixed pitch in which the vane pitch angle is fixed for a particular flight condition that provides the most fuel savings which, in one non-limiting embodiment may be a cruise condition. - In operation, the pitch angle of the
vane system 40 is set by thevane module 46 to increase propulsive efficiency to provide significant fuel savings; increase thrust at a given condition and power setting to provide improved take-off climb and cruise performance. Alternatively, the same thrust is achieved at a lower power setting which also increases engine life and fuel savings. - During landing, the pitch angle of the
vane system 40 is set by thevane module 46 to flat pitch which increases drag, reduces landing distance and reduces aircraft brake wear. That is, thevane system 40 operates as a speed brake in conjunction with, for example, thepropeller blade 32 pitch angle set to reverse pitch. - Furthermore, for other aircraft such as a tilt-rotor aircraft, the pitch angle of the
vane system 40 is set by thevane module 46 to a pitch based on an operating point flight condition such as hover flight to increase the efficiency of hover and low speed flight operations. - It should be understood that relative positional terms such as “forward,” “aft,” “upper,” “lower,” “above,” “below,” and the like are with reference to the normal operational attitude of the vehicle and should not be considered otherwise limiting.
- It should be understood that like reference numerals identify corresponding or similar elements throughout the several drawings. It should also be understood that although a particular component arrangement is disclosed in the illustrated embodiment, other arrangements will benefit herefrom.
- Although particular step sequences are shown, described, and claimed, it should be understood that steps may be performed in any order, separated or combined unless otherwise indicated and will still benefit from the present invention.
- The foregoing description is exemplary rather than defined by the limitations within. Various non-limiting embodiments are disclosed herein, however, one of ordinary skill in the art would recognize that various modifications and variations in light of the above teachings will fall within the scope of the appended claims. It is therefore to be understood that within the scope of the appended claims, the invention may be practiced other than as specifically described. For that reason the appended claims should be studied to determine true scope and content.
Claims (10)
1. A propulsion system comprising:
a propeller system which rotates about an axis of rotation; and
a rotationally fixed variable pitch vane system located axially aft of said propeller system.
2. The propulsion system as recited in claim 1 , wherein said propeller system includes a plurality of propeller blades and said rotationally fixed variable pitch vane system include a plurality of vanes.
3. The propulsion system as recited in claim 2 , wherein said plurality of propeller blades is equal to said plurality of vanes.
4. The propulsion system as recited in claim 2 , wherein each of said plurality of propeller blades define a diameter generally equal to a diameter of each of said plurality of vanes.
5. The propulsion system as recited in claim 1 , further comprising a vane module operable to collectively change a pitch of each of said plurality of vanes.
6. A flight control method for an aircraft:
collectively changing a pitch of a rotationally fixed variable pitch vane system located axially aft of a propeller system.
7. A method as recited in claim 6 , further comprising:
changing the pitch of the rotationally fixed variable pitch vane system to recover a swirl component generated by the propeller system.
8. A method as recited in claim 6 , further comprising:
changing the pitch of the rotationally fixed variable pitch vane system to provides maximum propulsive efficiency at a particular operating point.
9. A method as recited in claim 8 , further comprising:
defining the operating point at a cruise flight condition.
10. A method as recited in claim 6 , further comprising:
changing the pitch of the rotationally fixed variable pitch vane system to a flat pitch during a landing condition.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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US12/501,520 US20100014977A1 (en) | 2008-07-15 | 2009-07-13 | Variable pitch aft propeller vane system |
Applications Claiming Priority (2)
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US13491308P | 2008-07-15 | 2008-07-15 | |
US12/501,520 US20100014977A1 (en) | 2008-07-15 | 2009-07-13 | Variable pitch aft propeller vane system |
Publications (1)
Publication Number | Publication Date |
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US20100014977A1 true US20100014977A1 (en) | 2010-01-21 |
Family
ID=41058034
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US12/501,520 Abandoned US20100014977A1 (en) | 2008-07-15 | 2009-07-13 | Variable pitch aft propeller vane system |
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US (1) | US20100014977A1 (en) |
GB (2) | GB2461811B (en) |
Cited By (16)
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US20150291276A1 (en) * | 2012-10-23 | 2015-10-15 | General Electric Company | Unducted thrust producing system architecture |
US20160333729A1 (en) * | 2015-05-11 | 2016-11-17 | General Electric Company | Turbine engine having variable pitch outlet guide vanes |
US20170102006A1 (en) * | 2015-10-07 | 2017-04-13 | General Electric Company | Engine having variable pitch outlet guide vanes |
WO2022018380A1 (en) * | 2020-07-23 | 2022-01-27 | Safran Aircraft Engines | Turbine engine module equipped with a propeller and stator vanes supported by retaining means and corresponding turbine engine |
US11492918B1 (en) | 2021-09-03 | 2022-11-08 | General Electric Company | Gas turbine engine with third stream |
WO2022228734A3 (en) * | 2021-04-26 | 2023-03-23 | Malte Schwarze | Efficiently generating thrust |
EP4155506A1 (en) * | 2021-09-26 | 2023-03-29 | Malte Schwarze | Efficient thrust generation |
US11680530B1 (en) | 2022-04-27 | 2023-06-20 | General Electric Company | Heat exchanger capacity for one or more heat exchangers associated with a power gearbox of a turbofan engine |
US11686211B2 (en) | 2021-08-25 | 2023-06-27 | Rolls-Royce Corporation | Variable outlet guide vanes |
US20230220816A1 (en) * | 2022-01-07 | 2023-07-13 | General Electric Company | Outlet guide vane |
US20230323789A1 (en) * | 2022-04-11 | 2023-10-12 | General Electric Company | Gas turbine engine with third stream |
US11788429B2 (en) | 2021-08-25 | 2023-10-17 | Rolls-Royce Corporation | Variable tandem fan outlet guide vanes |
US11802490B2 (en) | 2021-08-25 | 2023-10-31 | Rolls-Royce Corporation | Controllable variable fan outlet guide vanes |
US11834995B2 (en) | 2022-03-29 | 2023-12-05 | General Electric Company | Air-to-air heat exchanger potential in gas turbine engines |
US11834992B2 (en) | 2022-04-27 | 2023-12-05 | General Electric Company | Heat exchanger capacity for one or more heat exchangers associated with an accessory gearbox of a turbofan engine |
US11879343B2 (en) | 2021-08-25 | 2024-01-23 | Rolls-Royce Corporation | Systems for controlling variable outlet guide vanes |
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US11300003B2 (en) | 2012-10-23 | 2022-04-12 | General Electric Company | Unducted thrust producing system |
US9771878B2 (en) * | 2015-10-19 | 2017-09-26 | General Electric Company | Thrust scheduling method for variable pitch fan engines and turbo-shaft, turbo-propeller engines |
GB2593417A (en) * | 2019-10-02 | 2021-09-29 | Advanced Mobility Res And Development Ltd | Systems and methods for aircraft |
FR3109140B1 (en) * | 2020-04-10 | 2022-04-29 | Safran | System for determining the angular setting of an annular row of stator vanes |
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Also Published As
Publication number | Publication date |
---|---|
GB2469769A (en) | 2010-10-27 |
GB0912343D0 (en) | 2009-08-26 |
GB201013244D0 (en) | 2010-09-22 |
GB2469769B (en) | 2011-02-23 |
GB2461811A (en) | 2010-01-20 |
GB2461811B (en) | 2010-09-22 |
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