CN101649758B - Energy consumption system used in the fracturing of turbine shaft of gas turbine engine - Google Patents
Energy consumption system used in the fracturing of turbine shaft of gas turbine engine Download PDFInfo
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- CN101649758B CN101649758B CN200810146282.0A CN200810146282A CN101649758B CN 101649758 B CN101649758 B CN 101649758B CN 200810146282 A CN200810146282 A CN 200810146282A CN 101649758 B CN101649758 B CN 101649758B
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- brake member
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- ring part
- wheel rim
- turbine
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Abstract
The invention relates to a device for braking a turbine in a gas turbine engine. The turbine comprises a rotor, wherein the rotor is provided with at least one wheel disc (63'); the wheel disc is provided with a wheel rim (63'B); the rotor drives a shaft and can rotate relatively to a stator; the braking device is used when the shaft is fractured, and comprises a first braking member (110) which is fixed to the wheel rim and is provided with at least one cutting device (110A), and a second braking member (120) which is fixed to the stator positioned below the wheel rim (63'B); the second braking member comprises a ring unit (120A), and a material selected by the ring unit can be cut off by a cutting piece (110A); once the shaft is fractured, two braking devices are contacted with each other through axial displacement of the rotor, and the cutting piece (110A) of the first braking member (110) can cut the ring unit (120A) of the second braking member (120).
Description
Technical field
The present invention relates to gas turbine engine field, particularly Multi-channel type turbojet engine field, and relate to a kind of system, described system can make turbo machine out of service within the time short as far as possible when turbine shaft ruptures.
Background technique
In a Multi-channel type turbofan, fan is driven by low-pressure turbine.When the axle fracture that fan propeller is connected with turbine rotor, the counter-torque acted on turbine will discharge suddenly, although drive combustion gas to continue flowing turbine power is transferred to rotor.This can cause rotor speed to increase sharply, and is easy to reach its lit range that can bear and damage, and catastrophic consequence can occur thereupon.
Someone proposes such scheme, and namely interrupt to firing chamber supply fuel, object removes energy source, and rotor can not be accelerated because lacking energy source.A solution is the rotating speed using redundant measurement device to carry out detection axis, once find that hypervelocity provides the instruction of failure of oil feed, according to U.S. US6494046 patent, rotational frequency can be measured at the bearing place at axle two ends, and carry out continuing to compare in real time to these frequencies.
In addition, be proposed that use when described accident occurs can the device of brake rotors.After axle fracture, the axial displacement of rotor can start actuator's action, and the object of this actuator is the described kinetic energy that dissipates.Such as, these mechanisms can be the fixing fins being positioned at contiguous guide vane (IGV) assembly, tilt to rotor blade direction, so that can between these blades and across in the middle of vane path.These parts rub each other, are out of shape, or even rupture and kinetic energy is dissipated.In EP1640564 patent application, such solution is described with the name of applicant.In this scheme, the stator blade near the turbine blade needing braking has installed individual breaking plant, and when rotor starts to move along downstream direction, these breaking plants can cut off the supporting leg of upstream rotor blade.
Although this solution is effective, maintenance expenses is caused greatly to increase due to the damage caused blade.
Summary of the invention
The present invention aims to provide a kind of simple, effective and with low cost solution, and to reduce the rotating speed of turbine in gas turbine engine, described turbine comprises the rotor of a live axle, and this rotor can rotate when described axle fracture in stator.
According to the present invention, the device being used for braking the turbine with rotor in gas turbine engine is a device including the first brake member and the second brake member, described rotor has the rotor disk of wheel rim with at least one, can drive an axle and can rotate relative to stator; Described first brake member to be fixed on described wheel rim and to be provided with at least one cutting member, described second brake member is then fixed on the stator in wheel rim downstream, it comprises an annular element, and described annular element adopts a kind of can being made by the material that the cutting member of the first brake member cuts away; Once axle fracture, by the axial displacement of rotor, and two brake members being positioned at fan airstream pipeline external are contacted with each other, namely the cutting member of the first brake member can cut away the annular element of the second brake member, described ring part is devised, to be dissipated the energy provided by rotor by such cutting.
Therefore, solution of the present invention is the energy of the rotor between dissipation two components, and these two components are used to provide braking action specially.These devices can increase area of contact according to required target, and provide very high friction factor.
In addition, the advantage of the program is, is minimized at the maximum (top) speed that the situation lower rotor part of damage can not be caused to have to bear.Described speed is the easy to reach velocity range when axle fracture.
Because brake member is positioned at fan airstream pipeline external, blade thus can not sustain damage, described energy dissipation is then limited to concrete region.
For the motor be made up of exit casing, the first component can be fixed to last turbine stage of rotor easily, and second component can be fixed on exit casing easily.
According to an embodiment, the first brake member comprises multiple cutting member around engine axis distribution, and these cutting members can process together with wheel rim.Cutting member is a kind of form of cutter, is used for cutting ring part, removes material.
According to another feature, ring part can be attached on the flange that is positioned on stator.
In addition, the invention still further relates to a twin spool gas turbine motor, with a low pressure turbine section, wherein, described low pressure turbine section is equipped with a braking device as above.Below in conjunction with accompanying drawing, and by the explanation of one embodiment of the present of invention, other features and advantages of the invention will display, but the present invention is not limited in described embodiment.
Accompanying drawing explanation
Fig. 1 shows the axial half-sectional view of twin spool gas turbine engine turbine section;
Fig. 2 shows the braking device formed in gas turbine engine low pressure turbine section.
Embodiment
Fig. 1 shows a part for gas-turbine unit turbine section 1.In double rotor bypass engine, turbine section 1 comprises a upstream high turbine (not shown), accepts the hot combustion gas from firing chamber.Through being directed to low pressure turbine section 5 by one group of stationary guide blades 3 after high pressure turbine wheel blade is flow through in combustion gas.This low pressure turbine section 5 is rotors 6, presents a kind of shape of wheel hub herein, is namely assembled (in this example, being three impeller plates) by several impeller plate 61,62,63.Blade assembly comprises blade and blade root, is generally arranged on one by one in the interior chamber formed of wheel rim of wheel disc periphery.Complete stationary guide blades 7 be stacked in turbine at different levels between, each level can suitably relative to the moving blade in downstream and the gas flow that leads.This assembly defines low pressure turbine section 5.The rotor 6 of low-pressure turbine is arranged on an axle 8 concentric with high-pressure shaft 9, and the latter extends to the front portion of motor, and this axle is fixed on fan propeller at this.Rotor assembly is by the corresponding bearings being positioned at motor front and rear part.Fig. 1 shows the axle 8 supported by structure casing-the be referred to as bearing 81 in exit casing 10-.Exit casing provides fixing device, can attach it on aircraft.
When axle 8 surprisingly ruptures, because gas institute applied pressure, the movable component of low-pressure turbine will move (as figure moves right) backward.In addition, when these hot gass are by turbine, because its counter-torque disappears simultaneously also because hot gas continues the tangential thrust that is applied on moving vane, its rotary motion is accelerated.
According to the present invention, in order to prevent turbine driving, the maximum (top) speed simultaneously also allowed before failure to prevent it from reaching, employs a braking device in turbine section.
Fig. 2 shows this device 100, and this figure is the fragmentary perspective view of turbine blade 63 ' and exit casing.
Leaf dish 63 ' is corresponding to wheel disc 63 shown in the Fig. 1 after adapted according to the invention.Wheel disc 63 ' is other traditional certain form, in this example, its peripheral position is provided with a wheel hub 63 ' A, a wheel rim 63 ' B, and between wheel hub and wheel rim, have a thin radial reinforcer 63 ' C.Wheel rim 63 ' B provides the fixing device of a leaf dish, and this device radially extend in annular pass, and propellant is walked in this passage.Blade and its fixing device do not form constituent element of the present invention, and do not have entirety to illustrate in the drawings, only can see profiled plan profile.Shown exit casing 10 is towards wheel disc 63 '.It comprises a ring-shaped platform 10A, and the latter constitutes the inwall of gas channel, is the continuity of wheel disc 63 ' the periphery platform of turbine final stage.Stator blade 10B radial direction extends in annular pass.Platform 10A axially extends to wheel disc 63 ' by the form of ring packing tenon 10A ' in upstream.
Introduce braking device 100 of the present invention below.This device comprises first brake member 110, and the latter is made up of cutting member 110A again.First brake member 110 is fixed on wheel rim 63 ' B.In this example, more particularly, the first brake member 110 is fixed on the radial flange parts 63 ' B1 of wheel rim downstream.According to example shown, the tooth of cutting member 110A tilts along the direction that wheel disc rotates.The far-end chamfering of cutting member, its shape defines a cutting device, such as a cut-off machine.In that case, cut edge is radial, or in fact radial.
Described first braking device (110) can be installed in addition with on the flange portion 63 ' B1 of wheel rim 63 ' B, but is formed while also can passing through to process wheel rim on foundry goods.In this case, its material and wheel rim Metal Phase used together, have the hardness of wheel rim.
Second brake member 120 is arranged on the stator that formed by exit casing 10.It comprises an annular flange flange 120B, and employing is bolted on the ring stiffener of lip 10A ' below exit casing 10.Annular flange flange 120B comprises a radial flange part 120B1, and it is positioned at the downstream of the first brake member 110.Ring part 120A is fixed on vibrating part 120B1.Described ring part 120A is rectangular section, and its sagittal plane is perpendicular to spin axis, and the downstream being fixed to the cut edge of cutting member (110A) is comparatively in short distance, and cutting member (110A) defines the first cutting element (110).
Selected by ring part 120A, material hardness is lower than the hardness of cutting member 110A.It can make an one-piece element with flange 120B, but also can be attached to completely on vibrating part.
When normally working, turbine wheel dish can rotate around its axis, and cutting member 110A is then around engine axis rotary motion, and parallel with the front of ring part 120A, had better not contact ring part.
When moving to downstream axial because of the fracture of axle 8 when wheel disc, cutting member 110A and the combination of ring part 120A need cutting member 110A to rub with ring part 120A phase.Under the effect of the pressure, this rotation can make cutting member 110A by traditional cutting tool mode to cut ring part 120A.Thering is provided of energy is because the rotation of rotor, so, this energy and being dissipated.
The geometrical shape of cutting member 110A; Groove angle, the length of cutting edge, and the material selected by them all should be considered to determine in conjunction with the material of ring part 120A together.
Claims (8)
1. in gas turbine engine to the device that the turbine with rotor is braked, described rotor has the rotor disk of wheel rim with at least one, can drive an axle can rotating relative to stator; Described device is used for using when described axle fracture, and it comprises the first brake member and the second brake member, described first brake member to be fixed on described wheel rim and to be provided with at least one cutting member, described second brake member is then fixed on the stator in wheel rim downstream, it comprises a ring part, and described ring part adopts and a kind ofly can be cut the material that part cuts away and make; Once axle fracture, by the axial displacement of rotor, and two brake members being positioned at fan airstream pipeline external are contacted with each other, namely the cutting member of the first brake member can cut away the ring part of the second brake member, described ring part is devised, and dissipates with the material being formed described ring part by cutting the energy provided by rotor.
2. device according to claim 1, motor comprises an exit casing, it is characterized in that, the first brake member is fixed to last turbine stage of rotor, and the second brake member is then fixed on exit casing.
3. according to device according to claim 1 or claim 2, it is characterized in that, the first brake member comprises multiple cutting member around engine axis distribution.
4. device according to claim 1, is characterized in that, the cutting member of the first brake member processes with wheel rim.
5. device according to claim 1, is characterized in that, cutting member machining on the optional feature being fixed to wheel rim of the first brake member forms.
6. according to claim 4 or device according to claim 5, it is characterized in that, cutting member is cutter form, is used in the ring part of incision second brake member, removes material.
7. according to the device in claim 1 and 2 described in any one claim, it is characterized in that, the ring part of the second brake member is attached on flange that stator is installed.
8. a twin-spool turbine engine with low pressure turbine section, wherein, the braking device before described low pressure stage is equipped with wherein described in a claim.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810146282.0A CN101649758B (en) | 2008-08-14 | 2008-08-14 | Energy consumption system used in the fracturing of turbine shaft of gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810146282.0A CN101649758B (en) | 2008-08-14 | 2008-08-14 | Energy consumption system used in the fracturing of turbine shaft of gas turbine engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101649758A CN101649758A (en) | 2010-02-17 |
| CN101649758B true CN101649758B (en) | 2015-05-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN200810146282.0A Active CN101649758B (en) | 2008-08-14 | 2008-08-14 | Energy consumption system used in the fracturing of turbine shaft of gas turbine engine |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10801361B2 (en) * | 2016-09-09 | 2020-10-13 | General Electric Company | System and method for HPT disk over speed prevention |
| CN113047959B (en) * | 2019-12-27 | 2022-07-12 | 中国航发商用航空发动机有限责任公司 | Aeroengine braking device and aeroengine |
| CN114165339B (en) * | 2020-09-10 | 2023-03-14 | 中国航发商用航空发动机有限责任公司 | Rotational speed limiting apparatus and method for turbine engine |
| CN114837752A (en) * | 2021-02-02 | 2022-08-02 | 中国航发商用航空发动机有限责任公司 | Aircraft engine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2966333A (en) * | 1957-06-27 | 1960-12-27 | Fairchild Engine & Airplane | Overspeed safety device for turbine wheels |
| US4498291A (en) * | 1982-10-06 | 1985-02-12 | Rolls-Royce Limited | Turbine overspeed limiter for turbomachines |
| US5029439A (en) * | 1988-12-15 | 1991-07-09 | Societe National D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Gas turbine engine including a turbine braking device |
| CN1755063A (en) * | 2004-09-28 | 2006-04-05 | 斯奈克玛公司 | Turbine overspeed limiting device |
-
2008
- 2008-08-14 CN CN200810146282.0A patent/CN101649758B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2966333A (en) * | 1957-06-27 | 1960-12-27 | Fairchild Engine & Airplane | Overspeed safety device for turbine wheels |
| US4498291A (en) * | 1982-10-06 | 1985-02-12 | Rolls-Royce Limited | Turbine overspeed limiter for turbomachines |
| US5029439A (en) * | 1988-12-15 | 1991-07-09 | Societe National D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Gas turbine engine including a turbine braking device |
| CN1755063A (en) * | 2004-09-28 | 2006-04-05 | 斯奈克玛公司 | Turbine overspeed limiting device |
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| Publication number | Publication date |
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| CN101649758A (en) | 2010-02-17 |
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