CN101649758A - 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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- CN101649758A CN101649758A CN200810146282A CN200810146282A CN101649758A CN 101649758 A CN101649758 A CN 101649758A CN 200810146282 A CN200810146282 A CN 200810146282A CN 200810146282 A CN200810146282 A CN 200810146282A CN 101649758 A CN101649758 A CN 101649758A
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- wheel rim
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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 the gas turbine engine field, particularly multichannel formula turbojet engine field, and relate to a kind of system, described system can make turbo machine out of service in the short as far as possible time when turbine shaft ruptures.
Background technique
In a multichannel formula turbofan, fan is driven by low-pressure turbine.When fan propeller during with axle fracture that turbine rotor links to each other, the resistance moment of torsion that acts on the turbine will discharge suddenly, continues to flow turbine power is transferred to rotor although drive combustion gas.This can cause that rotor speed increases sharply, and is easy to reach the lit range that it can bear and damage, and catastrophic consequence can take place thereupon.
Someone proposes such scheme, promptly interrupts to the firing chamber fuel supplying, and purpose is to remove energy source, makes rotor can not quicken because of lacking energy source.A solution is to use the redundant measurement device to detect the rotating speed of axle, in case provide the instruction of failure of oil feed when finding hypervelocity, according to U.S. US6494046 patent, can measure rotational frequency at the bearing place at axle two ends, and these frequencies are continued in real time relatively.
In addition, people also proposed when described accident takes place, to use can brake rotors device.The axial displacement meeting of rotor starts actuator's action behind the axle fracture, and the purpose of this actuator is the described kinetic energy that dissipates.For example, these mechanisms can be the fixedly fins that is positioned at contiguous guide vane (IGV) assembly, tilt to the rotor blade direction, so that can be between these blades and across in the middle of vane path.These parts rub each other, are out of shape, or even the fracture and make kinetic energy be dissipated.In the EP1640564 patent application, narrated such solution with the name of applicant.In this scheme, near the stator blade the turbine blade of needs brakings, individual breaking plant has been installed, when rotor begins when downstream direction moves, these breaking plants can be cut off the supporting leg of upstream rotor blade.
Although this solution is effective, owing to causing maintenance expenses to increase greatly to the damage that blade caused.
Summary of the invention
The present invention aims to provide a kind of simple, effectively and the cheap solution of cost, and to reduce the rotating speed of turbine in the gas turbine engine, described turbine comprises the rotor of a live axle, and this rotor can rotate in stator when described axle fracture.
According to the present invention, the device that is used in gas turbine engine the turbine that has rotor being braked is a device that has comprised first brake member and second brake member, described rotor has at least one rotor disk that wheel rim is arranged, and can drive an axle and also can rotate with respect to stator; Described first brake member is fixed on the described wheel rim and is provided with at least one cutting member, described second brake member then is 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 first brake member cuts away; In case during axle fracture, by the axial displacement of rotor, and make two brake members be in contact with one another, the cutting member of first brake member promptly can cut away the annular element of second brake member.
Therefore, solution of the present invention is the energy of the rotor between two members of dissipation, and these two members are to be used to provide braking action specially.These devices can increase area of contact according to required target, and very high friction factor is provided.
In addition, the advantage of this scheme is that the maximum (top) speed of having to bear at the situation lower rotor part that can not cause damage is minimized.Described speed is easy to reach velocity range when axle fracture.
Because brake member is positioned at fan airstream pipeline outside, thereby blade can not sustain damage, described energy dissipation then is limited to concrete zone.
For the motor of being made up of exit casing, first member can be fixed to last turbine stage of rotor easily, and second member can be fixed on the exit casing easily.
According to an embodiment, first brake member comprises a plurality of cutting members that distribute around engine axis, and these cutting members can process with wheel rim.Cutting member is a kind of form of cutter, is used for cutting ring part, removes material.
According to another characteristics, ring part can be attached on the flange that is positioned on the stator.
In addition, the invention still further relates to a double rotor gas turbine engine, have a low-pressure turbine section, wherein, described low-pressure turbine section is equipped with an aforesaid braking device.Below in conjunction with accompanying drawing, and the explanation by one embodiment of the present of invention, other characteristic of the present invention and advantage will display, but the present invention is not limited in described embodiment.
Description of drawings
Fig. 1 shows the axial half-sectional view of double rotor gas-turbine unit turbine section;
Fig. 2 shows a braking device that forms on gas turbine engine low-pressure turbine section.
Embodiment
Fig. 1 shows the part of gas-turbine unit turbine section 1.In double rotor bypass motor, turbine section 1 comprises a upstream high-pressure turbine (not shown), accepts the hot combustion gas from the firing chamber.Gas flow is crossed high pressure turbine wheel blade after be directed to low-pressure turbine section 5 by one group of stationary guide blades 3.This low-pressure turbine section 5 is rotors 6, presents a kind of shape of wheel hub herein, promptly by several impeller plates 61,62,63 be assembled (being three impeller plates in this example).Blade assembly comprises blade and blade root, generally is installed in one by one in the chamber that forms in the wheel rim of wheel disc periphery.Complete stationary guide blades 7 be stacked in turbine at different levels between, each grade can be suitably with respect to the moving blade in downstream and the gas flow that leads.This assembly has formed low-pressure turbine section 5.The rotor 6 of low-pressure turbine be installed in one with the concentric axle 8 of high-pressure shaft 9 on, the latter extends to the front portion of motor, and this axle is fixed on the fan propeller at this.Rotor assembly is by the corresponding bearings that is positioned at the motor front and rear part.Fig. 1 shows the axle 8 that is supported by structure casing-the be referred to as bearing 81 in the exit casing 10-.Exit casing provides fixing device, can attach it on the aircraft.
When axle 8 unexpected fractures, because gas institute applied pressure, the movable component of low-pressure turbine will move (moving right as figure) backward.In addition, when these hot gass when the turbine, because its resistance moment of torsion disappears simultaneously also because hot gas continues to be applied to the tangential thrust on the moving vane, its acceleration that rotatablely moves.
According to the present invention,,, in turbine section, used a braking device simultaneously also in order to prevent that it from reaching the maximum (top) speed that allows before damage in order to prevent the turbine driving.
Fig. 2 shows this device 100, and this figure is the part perspective view of whirlpool blade disk 63 ' and exit casing.
Introduce braking device 100 of the present invention below.This device comprises one first brake member 110, and the latter is made up of cutting member 110A again.First brake member 110 is fixed on the wheel rim 63 ' B.In this example, more particularly, 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 is to tilt along the direction that wheel disc rotates.The far-end chamfering of cutting member, its shape have formed a cutting device, such as a cut-off machine.Under this situation, the cut edge is radially, perhaps in fact is exactly radially.
Described first braking device (110) can increase on the flange portion 63 ' B1 that installs to wheel rim 63 ' B, but also can be by forming in the processing wheel rim on foundry goods.In this case, its material is identical with the used metal of wheel rim, has the hardness of wheel rim.
The selected material hardness of ring part 120A is lower than the hardness of cutting member 110A.It can make an one-piece element with flange 120B, but also can be attached on the vibrating part fully.
When proper functioning, the turbine wheel dish can be around the rotation of its axis, and cutting member 110A then rotatablely moves around engine axis, and positive parallel with ring part 120A, had better not contact ring part.
When wheel disc moved axially downstream because of the fracture of axle 8, the combination of cutting member 110A and ring part 120A needed cutting member 110A to rub mutually with ring part 120A.Under the effect of pressure, this rotation can make cutting member 110A cut ring part 120A by traditional cutting tool mode.Providing 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 their selected material all should be considered decision together in conjunction with the material of ring part 120A.
Claims (8)
1. device of in gas turbine engine, the turbine that has rotor being braked, described rotor has at least one rotor disk that wheel rim is arranged, and can drive an axle and can rotate with respect to stator; Described device is used for using when described axle fracture, and it comprises first brake member and second brake member, described first brake member is fixed on the described wheel rim and is provided with at least one cutting member, described second brake member then is fixed on the stator in wheel rim downstream, it comprises a ring part, and described ring part adopts and a kind ofly is cut the material that part cuts away and makes; In case during axle fracture, by the axial displacement of rotor, and make two brake members be in contact with one another, the cutting member of first brake member promptly can cut away the ring part of second brake member.
2. device according to claim 1, motor comprise an exit casing, it is characterized in that, first brake member is fixed to last turbine stage of rotor, and second brake member then is fixed on the exit casing.
3. according to claim 1 or the described device of claim 2, it is characterized in that first brake member comprises a plurality of cutting members that distribute around engine axis.
4. device according to claim 1 is characterized in that the cutting member of first brake member can process with wheel rim.
5. device according to claim 1 is characterized in that, the cutting member of first brake member can machining forms on the optional feature of wheel rim being fixed to.
6. according to claim 4 or the described device of claim 5, it is characterized in that cutting member is the cutter form, be used for cutting in the ring part of second brake member, remove material.
7. according to the described device of any one claim in claim 1 and 2, it is characterized in that the ring part of second brake member is attached on the flange of installing on the stator.
8. birotary burbine motor that has the low-pressure turbine section, wherein, described low pressure stage has been equipped wherein described braking device of claim of front.
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 true CN101649758A (en) | 2010-02-17 |
| CN101649758B CN101649758B (en) | 2015-05-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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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| CN (1) | CN101649758B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107806367A (en) * | 2016-09-09 | 2018-03-16 | 通用电气公司 | System and method for preventing disk from exceeding the speed limit |
| CN113047959A (en) * | 2019-12-27 | 2021-06-29 | 中国航发商用航空发动机有限责任公司 | Aeroengine braking device and aeroengine |
| CN114165339A (en) * | 2020-09-10 | 2022-03-11 | 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 |
Family Cites Families (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 |
| FR2640684B1 (en) * | 1988-12-15 | 1994-01-28 | Snecma | TURBOMACHINE COMPRISING A BRAKING DEVICE BETWEEN TURBINE ROTOR AND EXHAUST CASING |
| FR2875842B1 (en) * | 2004-09-28 | 2010-09-24 | Snecma Moteurs | DEVICE FOR LIMITING TURBINE OVERVIEW IN A TURBOMACHINE |
-
2008
- 2008-08-14 CN CN200810146282.0A patent/CN101649758B/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107806367A (en) * | 2016-09-09 | 2018-03-16 | 通用电气公司 | System and method for preventing disk from exceeding the speed limit |
| CN113047959A (en) * | 2019-12-27 | 2021-06-29 | 中国航发商用航空发动机有限责任公司 | Aeroengine braking device and aeroengine |
| 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 |
| CN114165339A (en) * | 2020-09-10 | 2022-03-11 | 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101649758B (en) | 2015-05-13 |
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