CN109667625A - It is a kind of for can backing turbine windage loss test cantilever rotor - Google Patents
It is a kind of for can backing turbine windage loss test cantilever rotor Download PDFInfo
- Publication number
- CN109667625A CN109667625A CN201910104891.8A CN201910104891A CN109667625A CN 109667625 A CN109667625 A CN 109667625A CN 201910104891 A CN201910104891 A CN 201910104891A CN 109667625 A CN109667625 A CN 109667625A
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- China
- Prior art keywords
- backing
- turbine
- backing turbine
- blade
- output shaft
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
Abstract
It is a kind of for can backing turbine windage loss test cantilever rotor, be related to a kind of cantilever rotor.The present invention solves conventional roulette+blade rotor test, and there are costly, period be long and two supports system structure and the relative complex problem of lubrication.Ahead moving blade piece (11) of the invention is mounted on turbine integral blade disc, backing turbine blade (12) is mounted on ahead moving blade piece (11) by intermediate ring (13), turbine integral blade disc, ahead moving blade piece (11), intermediate ring (13) and backing turbine blade (12) collectively constitute can backing turbine bilayer integral blade disc (1), can backing turbine output shaft (2) one end by dish axle connecting pin (3) with can backing turbine bilayer integral blade disc (1) connect, can backing turbine output shaft (2) one end suspension, can backing turbine bilayer integral blade disc (1) be located at the outsides of entire two bearing support fulcrums of rotor.The present invention can backing turbine windage loss test for gas turbine.
Description
Technical field
The present invention relates to a kind of cantilever rotors, and in particular to it is a kind of for can backing turbine windage loss test cantilever
Formula rotor.
Background technique
Gas turbine from the date of birth, just because power density is big, be swift in response the features such as, favored by various countries.As
The gas turbine of one of ship major impetus device, cannot directly move backward is the big defect of one.At present China's gas turbine fall
Vehicle problem is realized by displacement paddle.Although displacement paddle uses conventional gear box, and can provide the thrust control of balance,
But there are certain limitations and some disadvantages for it.Firstly, it, which transmits power, certain upper limit, more than paying after this power
Biggish cost.Secondly, normal with size, the weight ratio of the components such as the matched displacement paddle of heavy duty gas turbine, shafting and bearing
The constant-pitch propeller of rule is much greater, and costly.The bigger size of underwater component results in compared with constant pitch paddle
The construction complexity of the hull resistance for increasing by 10% under total power, the resistance of increase by 6% under cruise operation, and displacement paddle,
Maintenance difficulty is big, more complicated with system using that will make to design especially on heavy duty gas turbine.It can astern gas turbine
Appearance fundamentally solve these problems, i.e. the gas turbine ability simultaneously with forward and backward, astern power is by combustion gas wheel
Machine directly provides.
And the car-backing function of gas turbine be by can backing turbine realize that the movable vane piece of this turbine is by twi-tier blade
Composition, internal layer blade are positive vehicle turbo blade, and outer blade is backing turbine blade, and two layers of blade is connected, and pass through turbine
Disk and shaft power.When fuel gas flow all flows through internal layer blade, ahead turbine blade working, backing turbine blade at this time
Reversion；When fuel gas flow all flows through outer blade, backing turbine blade working, ahead turbine blade is inverted at this time.Obviously,
There is one layer of turbo blade to be in inverted status, especially unit always when unit operation and is chronically at ahead operation state, this
When, backing turbine blade can cause additional windage loss, and reduce unit uses power and efficiency.For this reason, it may be necessary to can
Backing turbine carries out windage loss and is studied.Although numerical computation technology it can be concluded that windage loss correlation values and rule
Rule, but more accurate test measurement is even more essential process.Due to traditional wheel disc+blade rotor structure, blade with
Individually machine adds wheel disc, and blade uses tenon groove structure using tenon structure, wheel disc, and tenon and tongue-and-groove processing capacity are relatively
Greatly, and the assembly work of blade and wheel disc is increased.Importantly, can backing turbine for the bilayer with the double-deck integral shroud
Movable vane, assembly difficulty are bigger.In addition, the rotor structure of two supports, needs that fuel feeding and oil return is respectively set to the both ends of bearing
Flow path and structure.Accordingly it is desirable to can have a kind of relatively easy structure, relative inexpensiveness and the strong rotor of realizability
Structure, can backing turbine windage loss test demand with satisfaction.
Summary of the invention
The present invention is in order to solve conventional roulette+blade rotor test, and there are costly, period be long and two supports
System structure and the relative complex problem of lubrication.Provide it is a kind of for can backing turbine windage loss test cantilevered turn
Son.
The technical scheme is that it is a kind of for can backing turbine windage loss test cantilever rotor, it includes whirlpool
Integral blade disc is taken turns, it further includes can backing turbine output shaft, dish axle connecting pin, ahead moving blade piece, intermediate ring and reversing whirlpool
Impeller blade, ahead moving blade piece are mounted on turbine integral blade disc, and backing turbine blade is mounted on ahead moving blade by intermediate ring
On piece, turbine integral blade disc, ahead moving blade piece, intermediate ring and backing turbine blade collectively constitute can the double-deck entirety of backing turbine
Fan disk, can backing turbine output shaft one end by dish axle connecting pin with can backing turbine bilayer integral blade disc connect,
Can backing turbine output shaft one end suspension, can backing turbine bilayer integral blade disc be located at two bearing support branch of entire rotor
The outside of point.
The present invention has following improvement effect compared with prior art:
The present invention is on the basis of making full use of traditional integral blade disc structural advantage, in conjunction with can backing turbine structure and work
Make feature, can backing turbine bilayer integral blade disc be used for backing turbine windage loss testpieces, and by adjusting rotor two
The axial position of a bearing support fulcrum obtains meeting rotor dynamics requirement, and the simple cantilever rotor structure of structure.Phase
Than traditional wheel disc+blade rotor structure, individually machine adds blade with wheel disc, and blade is used using tenon structure, wheel disc
Tenon groove structure, solve processing capacity it is big, with the double-deck integral shroud can backing turbine bilayer movable vane and wheel disc assembly difficulty asking greatly
Topic.In addition, the rotor structure relative to two supports, the support of cantilever rotor is located at the same side, is conducive to supply and recycle
Lubricating oil.For marine gas turbine can reverse power turbine test provide the relatively simple rotor structure of structure.
Detailed description of the invention
Fig. 1 be for can backing turbine windage loss test cantilever rotor schematic diagram；
Fig. 2 be can backing turbine bilayer integral blade disc side view；
Fig. 3 is direction view at the D of Fig. 2；
Fig. 4 is can backing turbine windage loss output shaft；
Fig. 5 is can backing turbine windage loss dish axle connecting pin；
Fig. 6 is the vane type line of backing turbine blade；
Fig. 7 is the vane type line of ahead moving blade piece；
Fig. 8 is the axial position schematic diagram of two bearing support fulcrums of rotor；
Fig. 9 is can backing turbine twi-tier blade angle schematic diagram.
Specific embodiment
Specific embodiment 1: illustrating present embodiment in conjunction with Fig. 1 to Fig. 4, one kind is used for can backing turbine windage loss
The cantilever rotor of test, it includes turbine integral blade disc, it further includes can backing turbine output shaft 2, dish axle connecting pin
3, ahead moving blade piece 11, intermediate ring 13 and backing turbine blade 12, ahead moving blade piece 11 are mounted on turbine integral blade disc,
Vehicle turbo blade 12 is mounted on ahead moving blade piece 11 by intermediate ring 13, turbine integral blade disc, ahead moving blade piece 11, centre
Ring 13 and backing turbine blade 12 collectively constitute can backing turbine bilayer integral blade disc 1, can backing turbine output shaft 2 one end
By dish axle connecting pin 3 with can backing turbine bilayer integral blade disc 1 connect, can backing turbine output shaft 2 one end suspension,
Can backing turbine bilayer integral blade disc 1 be located at the outsides of entire two bearing support fulcrums of rotor.
Cantilever rotor of the invention uses cantilever structure, can backing turbine bilayer integral blade disc 1 be located at it is entire
Two bearing support fulcrums of rotor are detailed in the outside of black triangle in Fig. 8.This rotor not only can satisfy backing turbine drum
Windage loss loses test requirements document, and structure is relatively easy, is conducive to meet test demand with lower cost.
Specific embodiment 2: illustrating present embodiment, 11 He of ahead moving blade piece of present embodiment in conjunction with Fig. 1 and Fig. 9
The blade profile tendency of backing turbine blade 12 is contrary.So set, power output when can satisfy different rotation directions, from
And have positive vehicle and car-backing function.Other compositions and connection relationship are same as the specific embodiment one.
Included angle A between the ahead moving blade piece 11 of present embodiment and the blade face of backing turbine blade 12 is 126 degree.
Specific embodiment 3: be illustrated in combination with fig. 1 and fig. 4 present embodiment, present embodiment can backing turbine output
Axis 2 is multi-diameter shaft, and can the diameter of backing turbine output shaft 2 be sequentially reduced from left to right.So set, being convenient for the installation of bearing
And axially position.Other compositions and connection relationship are the same as one or two specific embodiments.
Specific embodiment 4: illustrate present embodiment in conjunction with Fig. 3 and Fig. 4, the turbine integral blade disc of present embodiment,
The mass center of ahead moving blade piece 11, intermediate ring 13 and backing turbine blade 12 is located on same axis.So set, being conducive to subtract
The small centrifugal force because of caused by centroid motion.Other compositions and connection relationship are identical as specific embodiment one, two or three.
Specific embodiment 5: illustrating that present embodiment, present embodiment further include axial bearing gear in conjunction with Fig. 1 and Fig. 8
Block 4, transverse bearing prevent nut 5, bear box from preventing nut 9 and axial bearing block 6, and axial bearing block 4 is sleeved on can
The left side of backing turbine output shaft 2, bear box prevents nut 9 from being mounted on can be on backing turbine output shaft 2, and bear box hinders
Only nut 9 is located at the right side that transverse bearing prevents nut 5, and transverse bearing prevents nut 5 from being mounted on can backing turbine output shaft 2
On, and transverse bearing prevents nut 5 from being located at the right end of axial bearing block 4, axial bearing block 6 be sleeved on can backing turbine it is defeated
The right side of shaft 2.So set, realizing the axial restraint of bearing with relatively simple structure, and be conducive to adjust two branch
The distance between hold.Other compositions and connection relationship and specific embodiment one, two, three or four are identical.
Specific embodiment 6: illustrating present embodiment, the first support shaft fulcrum of present embodiment in conjunction with Fig. 1 and Fig. 8
Be arranged in transverse bearing prevent nut 5 and bear box prevent between nut 9 can be on backing turbine output shaft 2.So set,
Be conducive to the positioning of transverse bearing and rotor dynamics is adjusted by front support point.Other compositions and connection relationship and tool
Body embodiment one, two, three, four or five are identical.
Specific embodiment 7: illustrating present embodiment, the second support shaft fulcrum of present embodiment in conjunction with Fig. 1 and Fig. 8
Be arranged in 6 left end of axial bearing block can be on backing turbine output shaft 2.So set, be conducive to axial bearing positioning and
Rotor dynamics is adjusted by rear support point.Other compositions and connection relationship and specific embodiment one, two, three, four,
Five or six is identical.
Specific embodiment 8: embodiment is described with reference to Fig. 1, present embodiment further includes axial bearing inserts 7
Nut 10 is prevented with axial bearing, axial bearing inserts 7 is mounted on axial bearing block 6, and axial bearing prevents nut 10
Being mounted on can be on backing turbine output shaft 2, and axial bearing prevents nut 10 from being located at the right end of axial bearing block 6.So set
It sets, is conducive to the locking and dismounting of axial bearing.Other compositions and connection relationship and specific embodiment one, two, three, four, five,
Six or seven is identical.
Specific embodiment 9: embodiment is described with reference to Fig. 1, present embodiment further includes axial prevention pin 8, axial
Pin 8 is prevented to connect by axial between bearing block 6 and axial bearing inserts 7.So set, being conducive to the lock of axial bearing
Tight and dismounting.Other compositions and connection relationship and specific embodiment one, two, three, four, five, six or seven are identical.
The working principle of the invention:
The specific implementation steps are as follows:
(1) one layer of backing turbine blade 12 is added in the outer ring of conventional turbine integral blade disc movable vane, the backing turbine leaf
Piece molded line (see Fig. 5) tendency is opposite with original inner ring Blade Profile (see Fig. 6)；
(2) in set-up procedure (1) backing turbine vane type line axial direction and circumferential position, make upper and lower two layers of vane centroid
Positioned at same axis；
It (3) will with intermediate ring 13 be one between integral blade disc ahead moving blade piece 11 and backing turbine blade (12) ring
Body, composition can backing turbine bilayer integral blade discs 1；
It (4) can backing turbine bilayer integral blade disc 1 (being detailed in Fig. 2) and backing turbine output shaft 2 (being detailed in Fig. 3) use
Pin 3 (being detailed in Fig. 4) connection；
(5) fulcrum (being detailed in black triangle in Fig. 7) of entire two bearing supports of rotor is set, it can backing turbine pair
Layer integral blade disc 1 (being detailed in Fig. 2) is placed in the outer of two bearing support fulcrums of entire rotor (being detailed in black triangle in Fig. 7)
Side, can backing turbine bilayer integral blade disc 1 be located at the front end of axis, two bearing supports of rotor (are detailed in black three in Fig. 7
It is angular) be the double-deck integral blade disc 1 (being detailed in Fig. 2) rear side, constitute cantilever design；
(6) to step (5) obtain can backing turbine windage loss test cantilever rotor structure (being detailed in Fig. 1) carry out
Rotor dynamics calculates analysis；
(7) in set-up procedure (5) two bearing support fulcrums of rotor (being detailed in black triangle in Fig. 7) axial position
X1 and L repeats step (6) until obtaining and meets rotor dynamics requirement.
Using rotor of the invention, the rotation of backing turbine difference can be realized with relatively easy and lower-cost structure
Direction power output meets backing turbine windage loss test demand.
The above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations；Although with reference to the foregoing embodiments
Invention is explained in detail, those skilled in the art should understand that: it still can be to aforementioned each implementation
Technical solution documented by example is modified or equivalent replacement of some of the technical features；And these modification or
Replacement, the spirit and scope for technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution.
Claims (9)
1. it is a kind of for can backing turbine windage loss test cantilever rotor, it includes turbine integral blade disc, feature
Be: it further include can backing turbine output shaft (2), dish axle connecting pin (3), ahead moving blade piece (11), intermediate ring (13) and
Backing turbine blade (12), ahead moving blade piece (11) are mounted on turbine integral blade disc, during backing turbine blade (12) passes through
Between ring (13) be mounted on ahead moving blade piece (11), turbine integral blade disc, ahead moving blade piece (11), intermediate ring (13) and reversing
Turbo blade (12) collectively constitute can backing turbine bilayer integral blade disc (1), can one end of backing turbine output shaft (2) pass through
Dish axle connecting pin (3) with can backing turbine bilayer integral blade disc (1) connect, can backing turbine output shaft (2) one end it is outstanding
Set, can backing turbine bilayer integral blade disc (1) be located at the outsides of entire two bearing support fulcrums of rotor.
2. it is according to claim 1 it is a kind of for can backing turbine windage loss test cantilever rotor, it is characterised in that: just
Vehicle movable vane piece (11) and the blade profile tendency of backing turbine blade (12) are contrary.
3. it is according to claim 2 it is a kind of for can backing turbine windage loss test cantilever rotor, it is characterised in that: can
Backing turbine output shaft (2) is multi-diameter shaft, and can the diameter of backing turbine output shaft (2) be sequentially reduced from left to right.
4. it is according to claim 3 it is a kind of for can backing turbine windage loss test cantilever rotor, it is characterised in that: whirlpool
The mass center for taking turns integral blade disc, ahead moving blade piece (11), intermediate ring (13) and backing turbine blade (12) is located at same axis
On.
5. it is according to claim 4 it is a kind of for can backing turbine windage loss test cantilever rotor, it is characterised in that: it
It further include axial bearing block (4), transverse bearing prevention nut (5), bear box prevention nut (9) and axial bearing block
(6), axial bearing block (4) be sleeved on can backing turbine output shaft (2) left side, bear box prevent nut (9) be mounted on
Can be on backing turbine output shaft (2), and bear box prevents nut (9) from being located at the right side that transverse bearing prevents nut (5), radially
Bearing prevents nut (5) from being mounted on can be on backing turbine output shaft (2), and transverse bearing prevents nut (5) from being located at axial bearing
The right end of block (4), axial bearing block (6) be sleeved on can backing turbine output shaft (2) right side.
6. it is according to claim 5 it is a kind of for can backing turbine windage loss test cantilever rotor, it is characterised in that: the
One support shaft fulcrum setting transverse bearing prevent nut (5) and bear box prevention nut (9) between can backing turbine it is defeated
On shaft (2).
7. it is according to claim 6 it is a kind of for can backing turbine windage loss test cantilever rotor, it is characterised in that: the
Two support shaft fulcrums be arranged in axial bearing block (6) left end can be on backing turbine output shaft (2).
8. it is according to claim 7 it is a kind of for can backing turbine windage loss test cantilever rotor, it is characterised in that: it
It further include that axial bearing inserts (7) and axial bearing prevent nut (10), axial bearing inserts (7) is mounted on axial bearing
On block (6), axial bearing prevents nut (10) from being mounted on can be on backing turbine output shaft (2), and axial bearing prevents nut
(10) it is located at the right end of axial bearing block (6).
9. it is according to claim 8 it is a kind of for can backing turbine windage loss test cantilever rotor, it is characterised in that: it
Further include axial prevention pin (8), prevents to sell (8) even by axial between axial bearing block (6) and axial bearing inserts (7)
It connects.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910104891.8A CN109667625A (en) | 2019-02-01 | 2019-02-01 | It is a kind of for can backing turbine windage loss test cantilever rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910104891.8A CN109667625A (en) | 2019-02-01 | 2019-02-01 | It is a kind of for can backing turbine windage loss test cantilever rotor |
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| Publication Number | Publication Date |
|---|---|
| CN109667625A true CN109667625A (en) | 2019-04-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910104891.8A Pending CN109667625A (en) | 2019-02-01 | 2019-02-01 | It is a kind of for can backing turbine windage loss test cantilever rotor |
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| CN (1) | CN109667625A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110030043A (en) * | 2019-05-21 | 2019-07-19 | 中国船舶重工集团公司第七0三研究所 | It is a kind of for can backing turbine windage loss test support ring |
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