US20120328436A1 - Electromechanical actuator driven governor for ram air turbine - Google Patents
Electromechanical actuator driven governor for ram air turbine Download PDFInfo
- Publication number
- US20120328436A1 US20120328436A1 US13/167,801 US201113167801A US2012328436A1 US 20120328436 A1 US20120328436 A1 US 20120328436A1 US 201113167801 A US201113167801 A US 201113167801A US 2012328436 A1 US2012328436 A1 US 2012328436A1
- Authority
- US
- United States
- Prior art keywords
- sensor
- ram air
- turbine
- electromechanical actuator
- air turbine
- 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.)
- Abandoned
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D9/00—Adaptations of wind motors for special use; Combinations of wind motors with apparatus driven thereby; Wind motors specially adapted for installation in particular locations
- F03D9/20—Wind motors characterised by the driven apparatus
- F03D9/25—Wind motors characterised by the driven apparatus the apparatus being an electrical generator
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
- B64D41/007—Ram air turbines
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Definitions
- This disclosure relates to a ram air turbine system. More particularly, the disclosure relates to a speed governor for the ram air turbine system.
- a ram air turbine (RAT) system includes turbine having blades.
- a typical RAT has a governor that adjusts the pitch angle of the turbine blades over the speed range of the aircraft.
- the turbine blades control the output rotational speed delivered from the blades to an electrical generator and/or hydraulic pump that are designed to operate efficiently over a typical operating speed range.
- One type of governor includes a set of springs which acts against a set of counterweights to set a desired blade pitch angle.
- the springs are often large and only operate on the principle of mechanical force balance with the counterweights. In these types of systems, there is no external mechanism to set the blade pitch.
- Other blade pitch control governors have been developed that entirely eliminate mechanical control systems that incorporate counterweights.
- a ram air turbine governor includes a hub carrying multiple turbine blades.
- a sensor is configured to detect a parameter.
- a counterweight is coupled to at least one turbine blade and is configured to provide an input to the turbine blade in response to a centrifugal force to move the turbine blade from a first pitch position to a second pitch position.
- An electromechanical actuator is operatively coupled to the counterweight.
- a controller is in communication with the mechanical actuator and the sensor. The controller is configured to command the electromechanical actuator and move the turbine blade from the second pitch position to a third pitch position in response to the detected parameter.
- FIG. 1 is a perspective view of a RAT system in a deployed position.
- FIG. 2 is a perspective view of an example RAT system having a mechanical governor assembly and an electromechanical actuator.
- FIG. 3 is a schematic of an example RAT control system for the disclosed RAT system.
- FIG. 4 is another example RAT system having the mechanical governor assembly and an electromechanical actuator.
- FIG. 1 illustrates a RAT system 10 secured to an aircraft structure 12 by a housing 14 .
- the housing 14 pivotally supports a strut 16 supporting a case 17 at one end to which a turbine 18 is mounted.
- the turbine 18 includes blades 20 , which impart rotational drive to a generator 22 and a hydraulic pump 26 .
- An actuator 24 is interconnected between the strut 16 and the housing 14 .
- the RAT system 10 is illustrated in its deployed position.
- the blades 20 include a root 28 that is supported by the hub 19 by a bearing assembly 30 .
- the blades 20 are rotatable about their respective pitch axes.
- a counterweight 32 is coupled to each of the blades 20 , which bias the blades 20 from a first pitch position to a second pitch position in response to a force input due to the centrifugal forces on the counterweights 32 .
- the first pitch position corresponds to a fine pitch
- the second pitch position corresponds to a coarse pitch.
- the turbine 18 rotates at its maximum speed in the fine pitch position.
- the counterweights 32 govern the turbine speed by rotating the blades 20 to a coarser position as the speed reaches a predetermined threshold.
- Rotation of the hub 19 rotationally drives a drive shaft 50 , which in turn rotationally drives the generator 22 and pump 26 .
- a yolk plate assembly 34 cooperates with the counterweights 32 .
- a cam follower 36 provided on the counterweights 32 is arranged between first and second spaced apart members 42 , 44 of the yolk plate assembly 34 .
- the yolk plate assembly 34 moves linearly along guide pins 38 with rotation of the blades 20 .
- the yoke plate assembly 34 is affixed to a centrally located governor shaft 40 .
- a spring assembly 46 is arranged within a nose cone 48 .
- the spring assembly 46 which includes a pair of concentric coil springs in the example, applies a spring force on the yolk plate assembly 34 to counteract the centrifugal force created by the counterweights 32 . In this manner, the spring assembly 46 establishes a limit to the overspeed protection provided by the counterweights 32 .
- Such an arrangement provides overspeed protection of about ⁇ 10-20% of an overspeed design limit.
- An electromechanical actuator 52 is coupled to the governor shaft 40 to linearly move the yolk plate assembly 34 , which changes the pitch of the blades 20 to a third pitch position.
- a coupling device 54 is used to mechanically interconnect the electromechanical actuator 52 and the governor shaft 40 , if necessary.
- the electromechanical actuator 52 may be an acme screw, ball screw or other configuration that enables the use of a relatively small motor and prevents back-driving.
- the electromechanical actuator 52 may be powered by the generator 22 , in one example.
- the electromechanical actuator 52 communicates with one or more sensors and is used to increase (fine direction) or decrease (coarse direction) the pitch of the blades 20 in response to detected parameters from the sensors. For example, the electromechanical actuator 52 may refine the overspeed limit and/or manipulate the pitch of the blades 20 during other conditions, such as turbine start-up or blade vibrations.
- a schematic of a RAT control system 56 is schematically illustrated in FIG. 3 .
- a controller 58 communicates with the electromechanical actuator 52 .
- the blades 20 are subject to a blade pitch force 66 due to the RAM airflow over the blades 20 .
- This blade pitch force 66 is altered by a counterweight force 68 , which is limited by a governor spring force 70 , if governor springs are used.
- the electromechanical actuator 52 provides an input to the blades 20 to move the blades from the second pitch position to the third pitch position thereby commanding the blades 20 to a position other than that dictated by the force balance on the blades (i.e., airflow over blades, counterweights and, if used, governor springs).
- a speed sensor 60 , a condition sensor 62 and/or a vibration sensor 64 , for example, are in communication with the controller 58 .
- the speed sensor 60 may be indicative of air speed or the rotational speed of the turbine 18 .
- the speed sensor 60 is provided by speed sensor integrated with the generator 22 .
- the controller 58 is programmed to command the electromechanical actuator 52 to position the blades 20 such that the target overspeed limit is reached.
- the condition sensor 62 may be a sensor that detects a turbine start-up condition, such as deployment of the RAT.
- the condition sensor may be a switch that initiates RAT deployment.
- the controller 58 is programmed to command the electromechanical actuator 52 to position the blades 20 initially to position in which the hub 19 rotates most rapidly up to desired operating speed.
- the vibration sensor 64 is configured to detect undesired vibration in the RAT, for example, blade vibration.
- the controller 58 is programmed to command the electromechanical actuator 52 to position the blades 20 to a position that induces less vibration, for example, to a coarser blade pitch.
- FIG. 4 Another example RAT system 110 is illustrated in FIG. 4 .
- the blades 120 are mounted on the hub 119 .
- the counterweights 132 automatically rotate the blades 120 from a first pitch position to a second pitch position in response to centrifugal force on the counterweights 132 .
- the yolk plate assembly 134 is coupled to the counterweights 132 via the cam followers 136 .
- the coupling device 154 interconnects the governor shaft 140 and the electromechanical actuator 152 .
- the electromechanical actuator 152 is arranged in the nose cone 148 instead of the case 117 , as illustrated in the example of FIG. 2 .
- the electromechanical actuator 152 may be easier to package in the nose cone 148 , for example, and the governor springs may be eliminated.
Abstract
A ram air turbine governor includes a hub carrying multiple turbine blades. A sensor is configured to detect a parameter. A counterweight is coupled to at least one turbine blade and is configured to provide an input to the turbine blade in response to a centrifugal force to move the turbine blade from a first pitch position to a second pitch position. An electromechanical actuator is operatively coupled to the counterweight. A controller is in communication with the mechanical actuator and the sensor. The controller is configured to command the electromechanical actuator and move the turbine blade from the second pitch position to a third pitch position in response to the detected parameter.
Description
- This disclosure relates to a ram air turbine system. More particularly, the disclosure relates to a speed governor for the ram air turbine system.
- A ram air turbine (RAT) system includes turbine having blades. A typical RAT has a governor that adjusts the pitch angle of the turbine blades over the speed range of the aircraft. The turbine blades control the output rotational speed delivered from the blades to an electrical generator and/or hydraulic pump that are designed to operate efficiently over a typical operating speed range.
- One type of governor includes a set of springs which acts against a set of counterweights to set a desired blade pitch angle. The springs are often large and only operate on the principle of mechanical force balance with the counterweights. In these types of systems, there is no external mechanism to set the blade pitch. Other blade pitch control governors have been developed that entirely eliminate mechanical control systems that incorporate counterweights.
- A ram air turbine governor includes a hub carrying multiple turbine blades. A sensor is configured to detect a parameter. A counterweight is coupled to at least one turbine blade and is configured to provide an input to the turbine blade in response to a centrifugal force to move the turbine blade from a first pitch position to a second pitch position. An electromechanical actuator is operatively coupled to the counterweight. A controller is in communication with the mechanical actuator and the sensor. The controller is configured to command the electromechanical actuator and move the turbine blade from the second pitch position to a third pitch position in response to the detected parameter.
- The disclosure can be further understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:
-
FIG. 1 is a perspective view of a RAT system in a deployed position. -
FIG. 2 is a perspective view of an example RAT system having a mechanical governor assembly and an electromechanical actuator. -
FIG. 3 is a schematic of an example RAT control system for the disclosed RAT system. -
FIG. 4 is another example RAT system having the mechanical governor assembly and an electromechanical actuator. -
FIG. 1 illustrates aRAT system 10 secured to anaircraft structure 12 by ahousing 14. Thehousing 14 pivotally supports astrut 16 supporting acase 17 at one end to which aturbine 18 is mounted. Theturbine 18 includesblades 20, which impart rotational drive to agenerator 22 and ahydraulic pump 26. Anactuator 24 is interconnected between thestrut 16 and thehousing 14. TheRAT system 10 is illustrated in its deployed position. - An
example RAT system 10 is illustrated inFIG. 2 . Theblades 20 include aroot 28 that is supported by thehub 19 by abearing assembly 30. Theblades 20 are rotatable about their respective pitch axes. Acounterweight 32 is coupled to each of theblades 20, which bias theblades 20 from a first pitch position to a second pitch position in response to a force input due to the centrifugal forces on thecounterweights 32. In one example, the first pitch position corresponds to a fine pitch, and the second pitch position corresponds to a coarse pitch. Theturbine 18 rotates at its maximum speed in the fine pitch position. Thus, thecounterweights 32 govern the turbine speed by rotating theblades 20 to a coarser position as the speed reaches a predetermined threshold. Rotation of thehub 19 rotationally drives adrive shaft 50, which in turn rotationally drives thegenerator 22 and pump 26. - A
yolk plate assembly 34 cooperates with thecounterweights 32. In particular, acam follower 36 provided on thecounterweights 32 is arranged between first and second spaced apartmembers yolk plate assembly 34. Theyolk plate assembly 34 moves linearly alongguide pins 38 with rotation of theblades 20. Theyoke plate assembly 34 is affixed to a centrally locatedgovernor shaft 40. - A
spring assembly 46 is arranged within anose cone 48. Thespring assembly 46, which includes a pair of concentric coil springs in the example, applies a spring force on theyolk plate assembly 34 to counteract the centrifugal force created by thecounterweights 32. In this manner, thespring assembly 46 establishes a limit to the overspeed protection provided by thecounterweights 32. Such an arrangement provides overspeed protection of about ±10-20% of an overspeed design limit. - An
electromechanical actuator 52 is coupled to thegovernor shaft 40 to linearly move theyolk plate assembly 34, which changes the pitch of theblades 20 to a third pitch position. Acoupling device 54 is used to mechanically interconnect theelectromechanical actuator 52 and thegovernor shaft 40, if necessary. Theelectromechanical actuator 52 may be an acme screw, ball screw or other configuration that enables the use of a relatively small motor and prevents back-driving. Theelectromechanical actuator 52 may be powered by thegenerator 22, in one example. - The
electromechanical actuator 52 communicates with one or more sensors and is used to increase (fine direction) or decrease (coarse direction) the pitch of theblades 20 in response to detected parameters from the sensors. For example, theelectromechanical actuator 52 may refine the overspeed limit and/or manipulate the pitch of theblades 20 during other conditions, such as turbine start-up or blade vibrations. - A schematic of a
RAT control system 56 is schematically illustrated inFIG. 3 . Acontroller 58 communicates with theelectromechanical actuator 52. Theblades 20 are subject to ablade pitch force 66 due to the RAM airflow over theblades 20. Thisblade pitch force 66 is altered by acounterweight force 68, which is limited by agovernor spring force 70, if governor springs are used. Theelectromechanical actuator 52 provides an input to theblades 20 to move the blades from the second pitch position to the third pitch position thereby commanding theblades 20 to a position other than that dictated by the force balance on the blades (i.e., airflow over blades, counterweights and, if used, governor springs). - A
speed sensor 60, acondition sensor 62 and/or avibration sensor 64, for example, are in communication with thecontroller 58. Thespeed sensor 60 may be indicative of air speed or the rotational speed of theturbine 18. In one example, thespeed sensor 60 is provided by speed sensor integrated with thegenerator 22. Thecontroller 58 is programmed to command theelectromechanical actuator 52 to position theblades 20 such that the target overspeed limit is reached. - The
condition sensor 62 may be a sensor that detects a turbine start-up condition, such as deployment of the RAT. In one example, the condition sensor may be a switch that initiates RAT deployment. Thecontroller 58 is programmed to command theelectromechanical actuator 52 to position theblades 20 initially to position in which thehub 19 rotates most rapidly up to desired operating speed. - The
vibration sensor 64 is configured to detect undesired vibration in the RAT, for example, blade vibration. Thecontroller 58 is programmed to command theelectromechanical actuator 52 to position theblades 20 to a position that induces less vibration, for example, to a coarser blade pitch. - Another
example RAT system 110 is illustrated inFIG. 4 . Theblades 120 are mounted on thehub 119. Thecounterweights 132 automatically rotate theblades 120 from a first pitch position to a second pitch position in response to centrifugal force on thecounterweights 132. Theyolk plate assembly 134 is coupled to thecounterweights 132 via thecam followers 136. Thecoupling device 154 interconnects thegovernor shaft 140 and theelectromechanical actuator 152. Theelectromechanical actuator 152 is arranged in thenose cone 148 instead of thecase 117, as illustrated in the example ofFIG. 2 . Theelectromechanical actuator 152 may be easier to package in thenose cone 148, for example, and the governor springs may be eliminated. - Although an example embodiment has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of the claims. For that reason, the following claims should be studied to determine their true scope and content.
Claims (10)
1. A ram air turbine governor comprising:
a hub carrying multiple turbine blades;
a sensor configured to detect a parameter;
a counterweight coupled to at least one turbine blade and configured to provide a rotational input to the turbine blade in response to a centrifugal force to move the turbine blade from a first pitch position to a second pitch position;
an electromechanical actuator operatively coupled to the counterweight; and
a controller in communication with the electromechanical actuator and the sensor, the controller configured to command the electromechanical actuator and move the turbine blade from the second pitch position to a third pitch position in response to the detected parameter.
2. The ram air turbine governor according to claim 1 , comprising a yoke plate assembly coupled to the counterweight and movable linearly with rotation of the blades.
3. The ram air turbine governor according to claim 2 , comprising a governor spring cooperating with the yoke plate assembly and configured to provide a force counteracting the rotational input.
4. The ram air turbine governor according to claim 2 , comprising a governor shaft affixed to the yoke plate assembly, and the electromechanical actuator coupled to the governor shaft and configured to move the yoke plate assembly in response to the command.
5. The ram air turbine governor according to claim 2 , wherein the counterweight includes a cam follower coupled to the yoke plate assembly and configured to translate between linear and rotational movement of the yoke plate assembly and the blade, respectively.
6. The ram air turbine governor according to claim 1 , wherein the sensor is a speed sensor, and the parameter corresponds to a rotational speed of the hub.
7. The ram air turbine governor according to claim 1 , wherein the sensor is a start-up condition sensor, and the parameter is a start-up condition.
8. The ram air turbine governor according to claim 1 , wherein the sensor is a vibration sensor, and the parameter is a vibration of the blade.
9. A ram air turbine governor comprising:
a hub carrying multiple turbine blades;
a sensor configured to detect a parameter, the parameter including at least one of a start-up condition and a vibration condition;
an electromechanical actuator operatively coupled to the turbine blades; and
a controller in communication with the electromechanical actuator and the sensor, the controller configured to command the electromechanical actuator and move the turbine blade between pitch positions in response to the detected parameter.
10. The ram air turbine governor according to claim 9 , comprising a counterweight coupled to at least one turbine blade and configured to provide a rotational input to the turbine blade in response to a centrifugal force to move the turbine blade from a first pitch position to a second pitch position.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/167,801 US20120328436A1 (en) | 2011-06-24 | 2011-06-24 | Electromechanical actuator driven governor for ram air turbine |
GB1209543.6A GB2492206B (en) | 2011-06-24 | 2012-05-29 | Electromechanical actuator driven governor for a ram air turbine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/167,801 US20120328436A1 (en) | 2011-06-24 | 2011-06-24 | Electromechanical actuator driven governor for ram air turbine |
Publications (1)
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US20120328436A1 true US20120328436A1 (en) | 2012-12-27 |
Family
ID=46546134
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US13/167,801 Abandoned US20120328436A1 (en) | 2011-06-24 | 2011-06-24 | Electromechanical actuator driven governor for ram air turbine |
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US (1) | US20120328436A1 (en) |
GB (1) | GB2492206B (en) |
Cited By (19)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130253734A1 (en) * | 2012-03-23 | 2013-09-26 | Hamilton Sundstrand Corporation | Speed control for a fixed ptich ram air turbine |
EP2949870A1 (en) * | 2014-05-30 | 2015-12-02 | General Electric Company | Variable-pitch rotor with remote counterweights |
JP2015227660A (en) * | 2014-05-30 | 2015-12-17 | ゼネラル・エレクトリック・カンパニイ | Variable-pitch rotor with remote counterweights |
US9399522B2 (en) | 2014-02-20 | 2016-07-26 | Hamilton Sundstrand Corporation | Ram air turbine actuator |
US20170210490A1 (en) * | 2016-01-27 | 2017-07-27 | Hamilton Sundstrand Corporation | Ram air turbine health monitoring system |
US9878800B2 (en) | 2015-01-16 | 2018-01-30 | Hamilton Sundstrand Corporation | Rat mounting arrangement for a soft aircraft interface |
US20180050813A1 (en) * | 2016-08-16 | 2018-02-22 | Hamilton Sundstrand Corporation | Inflight stow of ram air turbine |
US9976636B2 (en) * | 2015-04-22 | 2018-05-22 | Hamilton Sundstrand Corporation | Locking mechanisms for ram air turbines |
US10072510B2 (en) | 2014-11-21 | 2018-09-11 | General Electric Company | Variable pitch fan for gas turbine engine and method of assembling the same |
US10093430B2 (en) | 2015-01-16 | 2018-10-09 | Hamilton Sundstrand Corporation | Rat frame for a soft aircraft interface |
US10100653B2 (en) | 2015-10-08 | 2018-10-16 | General Electric Company | Variable pitch fan blade retention system |
US10322815B1 (en) * | 2018-03-22 | 2019-06-18 | Hamilton Sundstrand Corporation | Stored electrical energy assisted ram air turbine (RAT) system |
CN110182355A (en) * | 2019-04-29 | 2019-08-30 | 中国航空工业集团公司金城南京机电液压工程研究中心 | One kind being used for flight safety Emergency power source system feather centrifugal governor device |
US20190329900A1 (en) * | 2018-04-30 | 2019-10-31 | Hamilton Sundstrand Corporation | Hybrid ram air turbine with in-line hydraulic pump and generator |
US10508558B2 (en) * | 2017-02-10 | 2019-12-17 | Hamilton Sundstrand Corporation | Ram air turbine blades |
CN114278389A (en) * | 2021-12-30 | 2022-04-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Ram air turbine blade pitch angle rapid adjusting device and method |
CN114275170A (en) * | 2021-12-30 | 2022-04-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Frame and frame integrated type RAT system |
US11674435B2 (en) | 2021-06-29 | 2023-06-13 | General Electric Company | Levered counterweight feathering system |
US11795964B2 (en) | 2021-07-16 | 2023-10-24 | General Electric Company | Levered counterweight feathering system |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
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DE102016111954A1 (en) * | 2016-06-30 | 2018-01-04 | Wobben Properties Gmbh | Pitch system of a wind turbine and wind turbine |
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US8066481B2 (en) * | 2009-04-20 | 2011-11-29 | Hamilton Sundstrand Corporation | Balancing a ram air turbine |
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GB0313563D0 (en) * | 2003-06-12 | 2003-07-16 | Smiths Group Plc | Ram air turbines |
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Cited By (25)
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---|---|---|---|---|
US8965659B2 (en) * | 2012-03-23 | 2015-02-24 | Hamilton Sundstrand Corporation | Speed control for a fixed pitch ram air turbine |
US20130253734A1 (en) * | 2012-03-23 | 2013-09-26 | Hamilton Sundstrand Corporation | Speed control for a fixed ptich ram air turbine |
US9399522B2 (en) | 2014-02-20 | 2016-07-26 | Hamilton Sundstrand Corporation | Ram air turbine actuator |
EP2949870A1 (en) * | 2014-05-30 | 2015-12-02 | General Electric Company | Variable-pitch rotor with remote counterweights |
JP2015227660A (en) * | 2014-05-30 | 2015-12-17 | ゼネラル・エレクトリック・カンパニイ | Variable-pitch rotor with remote counterweights |
CN105317736A (en) * | 2014-05-30 | 2016-02-10 | 通用电气公司 | Variable-pitch rotor with remote counterweights |
US9869190B2 (en) | 2014-05-30 | 2018-01-16 | General Electric Company | Variable-pitch rotor with remote counterweights |
US10072510B2 (en) | 2014-11-21 | 2018-09-11 | General Electric Company | Variable pitch fan for gas turbine engine and method of assembling the same |
US10093430B2 (en) | 2015-01-16 | 2018-10-09 | Hamilton Sundstrand Corporation | Rat frame for a soft aircraft interface |
US9878800B2 (en) | 2015-01-16 | 2018-01-30 | Hamilton Sundstrand Corporation | Rat mounting arrangement for a soft aircraft interface |
US9976636B2 (en) * | 2015-04-22 | 2018-05-22 | Hamilton Sundstrand Corporation | Locking mechanisms for ram air turbines |
US10100653B2 (en) | 2015-10-08 | 2018-10-16 | General Electric Company | Variable pitch fan blade retention system |
US20170210490A1 (en) * | 2016-01-27 | 2017-07-27 | Hamilton Sundstrand Corporation | Ram air turbine health monitoring system |
US10683105B2 (en) * | 2016-01-27 | 2020-06-16 | Hamilton Sundstrand Corporation | Ram air turbine health monitoring system |
US20180050813A1 (en) * | 2016-08-16 | 2018-02-22 | Hamilton Sundstrand Corporation | Inflight stow of ram air turbine |
US10787274B2 (en) * | 2016-08-16 | 2020-09-29 | Hamilton Sundstrand Corporation | Inflight stow of ram air turbine |
US10508558B2 (en) * | 2017-02-10 | 2019-12-17 | Hamilton Sundstrand Corporation | Ram air turbine blades |
US10322815B1 (en) * | 2018-03-22 | 2019-06-18 | Hamilton Sundstrand Corporation | Stored electrical energy assisted ram air turbine (RAT) system |
US20190329900A1 (en) * | 2018-04-30 | 2019-10-31 | Hamilton Sundstrand Corporation | Hybrid ram air turbine with in-line hydraulic pump and generator |
US10661913B2 (en) * | 2018-04-30 | 2020-05-26 | Hamilton Sundstrand Corporation | Hybrid ram air turbine with in-line hydraulic pump and generator |
CN110182355A (en) * | 2019-04-29 | 2019-08-30 | 中国航空工业集团公司金城南京机电液压工程研究中心 | One kind being used for flight safety Emergency power source system feather centrifugal governor device |
US11674435B2 (en) | 2021-06-29 | 2023-06-13 | General Electric Company | Levered counterweight feathering system |
US11795964B2 (en) | 2021-07-16 | 2023-10-24 | General Electric Company | Levered counterweight feathering system |
CN114278389A (en) * | 2021-12-30 | 2022-04-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Ram air turbine blade pitch angle rapid adjusting device and method |
CN114275170A (en) * | 2021-12-30 | 2022-04-05 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Frame and frame integrated type RAT system |
Also Published As
Publication number | Publication date |
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GB201209543D0 (en) | 2012-07-11 |
GB2492206A (en) | 2012-12-26 |
GB2492206B (en) | 2013-09-18 |
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