CN107013263A - A kind of ram-air turbine feathering starts speed adjusting gear - Google Patents
A kind of ram-air turbine feathering starts speed adjusting gear Download PDFInfo
- Publication number
- CN107013263A CN107013263A CN201710273412.6A CN201710273412A CN107013263A CN 107013263 A CN107013263 A CN 107013263A CN 201710273412 A CN201710273412 A CN 201710273412A CN 107013263 A CN107013263 A CN 107013263A
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- CN
- China
- Prior art keywords
- block
- centrifugal
- turbo blade
- spring
- ram
- 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.)
- Pending
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Classifications
-
- 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
- F01D19/00—Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
-
- 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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/02—Purpose of the control system to control rotational speed (n)
-
- 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
- F05D2270/00—Control
- F05D2270/60—Control system actuates means
- F05D2270/66—Mechanical actuators
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Wind Motors (AREA)
Abstract
The present invention relates to ram-air turbine technical field, more particularly to a kind of ram-air turbine feathering starts speed adjusting gear.Described mechanism includes spring (1), spring base (2), centrifuge block (4), centrifugal-block (5) and turbo blade (6), the root of turbo blade (6) is hinged on wheel hub (7), the root of centrifugation block (4) and turbo blade (6) is fixed, centrifugal-block (5) is fixed on centrifugation block (4), the barycenter of centrifugal-block (5) deviates hub axis, the two ends of spring (1) are connected with wheel hub (7) and spring base (2) respectively, rocking arm is provided with centrifugation block (4), the end contact of rocking arm and spring base (2).1), can be by the smaller of vane wheel oar disk diameter design, so as to reduce system weight and size in the case of identical arrives stream wind speed and transmission loss；2) can under more heavy load loaded starting, expand and use scope.
Description
Technical field
The present invention relates to ram-air turbine technical field, more particularly to a kind of ram-air turbine feathering starts governor
Structure.
Background technology
Ram-air turbine (RAT) system is a kind of Emergency power source device, applied to most airline carriers of passengers and part
Military aircraft.When aircraft is normally run, RAT systems close at it is standby in RAT cabins, when aircraft loses active force in the air
Under the case of emergency of auxiliary power, RAT is deployed into air-flow, and absorption air punching press kinetic energy is provided for aircraft key user and answered
The anxious energy.For proof load working stability, usual turbine interior has mechanical governing mechanism, and RAT working speeds is stable
Within the specific limits.
Currently, most RAT speed adjusting gears are inverse oar mode of speed regulation, although this speed adjusting gear can realize stabilization
The function of rotating speed, but because turbo blade initial settling angle is larger (being calculated with the blade tip string of a musical instrument, typically larger than 75 °), cause turbine
Act whole blade when turning and be in High Angle of Attack stall conditions, lift-drag ratio is very low, starting torque very little.This may cause two problems：
1. when arrives stream wind speed is low or when turbine rear-end transmission system and the larger load system moment of resistance, it is necessary to design bigger oar disk diameter
RAT provides enough starting torques, it means that the increase of system weight and size；2. the aircraft under emergency rating exists
RAT is started under heavy load state, possibly can not normally rise and turn, cause unpredictable consequence.
The content of the invention
Present invention solves the technical problem that being：System weight, guarantee system startup reliability height can be mitigated by providing one kind
Speed adjusting gear.
The technical scheme is that：A kind of ram-air turbine feathering starts speed adjusting gear, it is characterized in that：Described machine
Structure includes spring 1, spring base 2, centrifugation block 4, centrifugal-block 5 and turbo blade 6, and the root of turbo blade 6 is hinged on wheel hub 7,
The root of centrifugation block 4 and turbo blade 6 is fixed, and centrifugal-block 5 is fixed on centrifugation block 4, and the barycenter of centrifugal-block 5 deviates wheel hub
Axle center, the two ends of spring 1 are connected with wheel hub 7 and spring base 2 respectively, and rocking arm, rocking arm and spring base 2 are provided with centrifugation block 4
End contact.
Preferably, the initial settling angle of turbo blade 6 is full feathering state.
Preferably, the blade tip string of a musical instrument of turbo blade 6 takes 10 °~25 ° with turbine axis angle.
Preferably, spring 1 has an initial prestretching force F0, the power size tries to achieve according to below equation：
Wherein, J0For the product of inertia of centrifugation block 4, centrifugal-block 5 and turbo blade 6 in initial position, ω1Opened for blade
Begin the inverse corresponding secondary speed of oar, and referred to as turbine is against oar rotating speed, LT0The arm of force size for being extension spring pulling force in initial position.
Beneficial effects of the present invention are：1), can be straight by vane wheel oar disk in the case of identical arrives stream wind speed and transmission loss
It is smaller that footpath is designed, so as to reduce system weight and size；2) can under more heavy load loaded starting, expand and use scope.
Brief description of the drawings
Fig. 1 is front view of the invention；
Fig. 2 is stereogram of the invention.
Embodiment
As illustrated, described mechanism includes spring 1, spring base 2, bearing 3, centrifugation block 4, centrifugal-block 5, turbo blade
6 and wheel hub, the root of turbo blade 6 by bearing hinge connection on wheel hub 7, the axle of the axis of turbo blade 6 perpendicular to wheel hub 7
To turbo blade 6 can be rotatable around its axis, and turbo blade is around wheel hub axial rotation during turbine.Centrifugation block 4 is sleeved on whirlpool
The root of impeller blade 6, is fixedly connected with root, and centrifugal-block 5 is fixed on centrifugation block 4, and the barycenter of centrifugal-block 5 deviates hub spindle
The heart, the i.e. barycenter of centrifugal-block 5 is not on the axis of wheel hub 7.The two ends of spring 1 are connected with wheel hub 7 and spring base 2 respectively.From
It is provided with heart block 4 on rocking arm, rocking arm and bearing 3 is installed, the periphery of bearing 3 and the end contact of spring base 2, the design
The phase mutual friction of rocking arm and spring base 2 is reduced, the reliability of mechanism is improved.The initial settling angle of turbo blade 6 is feathering
State, the blade tip string of a musical instrument and the turbine axis angle of turbo blade 6 take 10 °~25 °.Spring 1, spring base 2, bearing 3, centrifugation block
4 and centrifugal-block 5 be respectively positioned in wheel hub, under turbo operating state, rotated with turbo blade 6 around hub axis.
When turbine is assembled, spring 1 has an initial prestretching force F0, the power size tries to achieve according to below equation：
Wherein, J0For the product of inertia of centrifugation block 4, centrifugal-block 5 and turbo blade 6 in initial position, ω1Opened for blade
Begin the inverse corresponding secondary speed of oar, and referred to as turbine is against oar rotating speed, LT0The arm of force size for being extension spring pulling force in initial position.
After RAT systems, which receive instruction, enters air-flow, turbo blade 6 starts around the axial rotation of wheel hub 7.Due to centrifugal-block 5
Barycenter deviate hub axis, so one can be produced while centrifugal-block 5 is around wheel hub axial rotation around the axis of turbo blade 6
Torque.As rotating speed is when rising to up to turbine against oar rotating speed, the torque around the axis of turbo blade 6 increases, and centrifugation block 4 drives
Horizontal deflection is entered in the root of turbo blade 6 around the axial direction of turbo blade 6.Meanwhile, the rocking arm on centrifugation block 4 also occurs inclined therewith
Turn, by the bearing 3 on rocking arm to the applying power of spring base 2, and then be applied on spring 1.Secondary speed continues to increase,
Turbo blade 6 continues inverse oar, to ensure that turbine can continue to accelerate under the sum velocity of speed of incoming flow and blade rotational speed, work as rotating speed
When reaching rated speed, turbine realizes stabilization of speed under two groups of dynamic balance states：Spring torque and the power around petiole axis
Square is balanced；Turbine wheel shaft output torque and backend load balance.RAT is completed after starting, the equal energy in entirely using envelope curve
Worked in nominal speed range, stable Emergency power source is provided to aircraft.
Claims (4)
1. a kind of ram-air turbine feathering starts speed adjusting gear, it is characterized in that：Described mechanism includes spring (1), spring base
(2), centrifugation block (4), centrifugal-block (5) and turbo blade (6), the root of turbo blade (6) are hinged on wheel hub (7), centrifugal-block
Seat (4) and the root of turbo blade (6) are fixed, and centrifugal-block (5) is fixed on centrifugation block (4), and the barycenter of centrifugal-block (5) deviates
Hub axis, the two ends of spring (1) are connected with wheel hub (7) and spring base (2) respectively, are provided with rocking arm on centrifugation block (4), are shaken
The end contact of arm and spring base (2).
2. a kind of ram-air turbine feathering according to claim 1 starts speed adjusting gear, it is characterized in that：Turbo blade
(6) initial settling angle is full feathering state.
3. a kind of ram-air turbine feathering according to claim 1 starts speed adjusting gear, it is characterized in that：Turbo blade
(6) the blade tip string of a musical instrument takes 10 °~25 ° with turbine axis angle.
4. a kind of ram-air turbine feathering according to claim 1 starts speed adjusting gear, it is characterized in that：Spring (1) has
There is an initial prestretching force F0, the power size tries to achieve according to below equation：
Wherein, J0For centrifugation block (4), the product of inertia of centrifugal-block (5) and turbo blade (6) in initial position, ω1For blade
Start the inverse corresponding secondary speed of oar, referred to as turbine is against oar rotating speed, LT0It is big for the arm of force of the extension spring pulling force in initial position
It is small.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710273412.6A CN107013263A (en) | 2017-04-21 | 2017-04-21 | A kind of ram-air turbine feathering starts speed adjusting gear |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710273412.6A CN107013263A (en) | 2017-04-21 | 2017-04-21 | A kind of ram-air turbine feathering starts speed adjusting gear |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107013263A true CN107013263A (en) | 2017-08-04 |
Family
ID=59447078
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710273412.6A Pending CN107013263A (en) | 2017-04-21 | 2017-04-21 | A kind of ram-air turbine feathering starts speed adjusting gear |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107013263A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4701104A (en) * | 1986-06-18 | 1987-10-20 | Sundstrand Corporation | Ram air turbine |
| CN101865050A (en) * | 2009-04-20 | 2010-10-20 | 哈米尔顿森德斯特兰德公司 | Balancing a ram air turbine |
| CN103291375A (en) * | 2012-03-02 | 2013-09-11 | 哈米尔顿森德斯特兰德公司 | Flyweight for ram air turbine |
| CN204327201U (en) * | 2014-12-10 | 2015-05-13 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of sensitive switch interlocking type turbine locking framework of ram-air turbine |
-
2017
- 2017-04-21 CN CN201710273412.6A patent/CN107013263A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4701104A (en) * | 1986-06-18 | 1987-10-20 | Sundstrand Corporation | Ram air turbine |
| CN101865050A (en) * | 2009-04-20 | 2010-10-20 | 哈米尔顿森德斯特兰德公司 | Balancing a ram air turbine |
| CN103291375A (en) * | 2012-03-02 | 2013-09-11 | 哈米尔顿森德斯特兰德公司 | Flyweight for ram air turbine |
| CN204327201U (en) * | 2014-12-10 | 2015-05-13 | 中国航空工业集团公司金城南京机电液压工程研究中心 | A kind of sensitive switch interlocking type turbine locking framework of ram-air turbine |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
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Application publication date: 20170804 |