CN105003303A - Supporting system for turbine part of gas turbine engine - Google Patents
Supporting system for turbine part of gas turbine engine Download PDFInfo
- Publication number
- CN105003303A CN105003303A CN201510348279.7A CN201510348279A CN105003303A CN 105003303 A CN105003303 A CN 105003303A CN 201510348279 A CN201510348279 A CN 201510348279A CN 105003303 A CN105003303 A CN 105003303A
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- support plate
- supporting plates
- pneumatic blade
- load support
- force bearing
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Abstract
The invention provides a supporting system for a turbine part of a gas turbine engine. The supporting system comprises a bearing pedestal, a force bearing receiver and a plurality of force bearing supporting plates which are used for connecting the bearing pedestal and the force bearing receiver and are evenly distributed in the circumferential direction. Pneumatic blade type supporting plates are arranged outside the portions, located on an inner duct, of the force bearing supporting plates. The pneumatic blade type supporting plates are each of a cavity structure. The force bearing supporting plates are located in cavities of the pneumatic blade type supporting plates, and each pneumatic blade type supporting plate is provided with an air outlet. According to the supporting system, the portions, located in high-temperature and high-pressure gas, of the force bearing supporting plates are ingeniously provided with the pneumatic blade type supporting plates, and further, the pneumatic blade type supporting plates are arranged to be in the shape of wings; cooling gas coming from the inner cavities of the force bearing supporting plates can directly enter the pneumatic blade type supporting plates and has a cooling effect on the pneumatic blade type supporting plates; the inner sides and the outer sides of the force bearing supporting plates located in the inner cavities of the pneumatic blade type supporting plates are cooled; and besides, the pneumatic blade type supporting plates and gas located between the pneumatic blade type supporting plates and the force bearing supporting plates powerfully protect the force bearing supporting plates, and therefore the service life of the force bearing supporting plates is prolonged and the reliability of the force bearing supporting plates is improved.
Description
Technical field
The present invention relates to turbine technology field, more specifically, relate to a kind of supporting system for gas-turbine unit turbine parts.
Background technique
The rotor-support-foundation system of gas turbine engine and ground combustion machine, the load of its work needs to be delivered to outside motor by load supporting system and installs on joint.The load supporting system of rotor is made up of bearing support, load support plate, support case usually.Bearing support is for installing bearing and cooling thereof, lubricating structure; Support case is installed to save with motor by outside casing and is connected; Load support plate is used for coupling shaft bearing and support case.By-pass air duct refers to that circle duct outside suction port, is not connected with firing chamber; Main duct refers to that circle duct inside suction port, is connected with firing chamber.The air of main duct is by flowing in combustion chamber and fuel mix, and work by combustion, the air of by-pass air duct does not enter firing chamber, but mixes rear discharge mutually with the combustion gas that main duct flows out.The air of by-pass air duct is only by fan, and flow velocity is comparatively slow, and is low temperature, and what main duct was discharged is high-temperature fuel gas.
For turbine part, load support plate will through by-pass air duct and main duct, namely load support plate be positioned at the part of main duct will through high-temperature fuel gas passage, and bearing seat is in high-temperature fuel gas channel interior.Supporting structure particularly between high and low pressure turbine, its Maximum operating temperature can reach 1000 DEG C, and operating conditions is very severe.In order to ensure structural life-time and the reliability of load supporting system, common way adopts the better high-temperature alloy material of temperature resistant capability, or load support plate is made hollow-core construction, leads to cooling-air cool load support plate and bearing support from support plate inner chamber.
In prior art, adopt the better high-temperature alloy material of temperature resistant capability, the rising of cost must be brought.Lead to cooling-air from support plate inner chamber to cool, although can reduce the temperature of load supporting system to a certain extent, cooling effect is limited; Simultaneously because Temperature difference inside and outside support plate is comparatively large, very large thermal stress can be produced, cause load support plate to occur the faults such as crackle.
Summary of the invention
The technical problem to be solved in the present invention is to overcome load support plate in existing supporting system and is easily cracked by high temperature channel, for adopting High-temperature resistant alloy material dull load support plate high cost technical problem to anti-adverse environment, a kind of supporting system for gas-turbine unit turbine parts is provided, based on the optimal design-aside of this system architecture, ensure that the working environment of load support plate improves, good cooling results, life-span is longer, can avoid using resistant to elevated temperatures alloy material to make cost lower simply.
Above-mentioned purpose of the present invention is achieved by the following technical programs:
A kind of supporting system for gas-turbine unit turbine parts is provided, described supporting system comprises the uniform multiple load support plates of circumference of bearing support, support case and coupling shaft bearing and support case, and described load support plate is through the by-pass air duct of turbine part and main duct; Described load support plate is cavity structure, and the part that load support plate is positioned at by-pass air duct has suction port, and load support plate has air outlet near bearing support place; The present invention creatively has pneumatic blade profile support plate at described load support plate through the outer installment of the part of main duct, described pneumatic blade profile support plate is provided with cavity, load support plate is positioned at the cavity of pneumatic blade profile support plate through the part of main duct, and pneumatic blade profile support plate has air outlet.
Key improvements of the present invention is there is pneumatic blade profile support plate at load support plate through the outer installment of the part of main duct; make load support plate be positioned at pneumatic blade profile support plate cavity through the part of main duct, pneumatic blade profile support plate plays as the armor effect that protection is arranged in the load support plate of its cavity.
Preferably, described pneumatic blade profile support plate is airfoil structure.Described pneumatic blade profile support plate is set to as aerofoil profile by the present invention further, play its structure in aerodynamic characteristic excellent in aerodynamic force, effective reduction air-flow pitot loss, reduces the aerodynamic loading of whole supporting system, thus improves its life-span and operational safety while improving pneumatic efficiency.When air-flow is by aerofoil profile pneumatic blade profile support plate, the pressure from air-flow that pneumatic blade profile support plate is subject to is very little, and the pneumatic blade profile support plate of aerofoil profile plays as the armor effect that protection is arranged in the load support plate of its cavity.
The supporting system that the present invention adopts, pneumatic channel be separated with load supporting system, pneumatic blade profile support plate utilizes panel beating or casting to realize pneumatic modelling, forms blast tube with main duct; Load support plate props up intralamellar part from pneumatic blade profile and passes, and is inside and outsidely connected with bearing support and support case respectively.First the cooling-air attracted from engine front enters load support plate inner chamber from load support plate suction port through by-pass air duct, enters the cooling that the cavity of sprue (by-pass air duct and main duct) between inwall and bearing support realizes load support plate and bearing support; Cooling-air enters the Cavity Flow between load support plate gentle movable vane type support plate through load support plate air outlet more afterwards, realizes isolating to main flow combustion gas and supporting system, and the air outlet finally again on pneumatic blade profile support plate enters sprue and continues to participate in acting.
Further preferably, the cross section of described load support plate is racetrack.Cross section is the load support plate of racetrack is preferred character structure provided by the invention, and manufacturing is simple, and bearing capacity is up to standard, and geometric space utilization ratio is large, and can reach required Throughput requirement as required.
Preferably, described supporting system also comprises center tracheae, and described center tracheae is positioned at the cavity of described load support plate.In load support plate cavity, the effect that center tracheae plays transmission is set.Load support plate is connected with bearing support, and for ensureing the requirement such as the working life of bearing and the stability of system architecture, need lubricate bearing, the present invention adds center tracheae, adds lubricant oil to bearing by center tracheae; In order to balance the air pressure in load support plate, be communicated with barometric pressure by center tracheae; Sometimes need to detect back-up system inside, also by center tracheae, detection device is inserted.
Preferably, the quantity of described center tracheae is 4 ~ 9, and each center tracheae is arranged in a described load support plate cavity.Described center tracheae is respectively used to for bearing oil, lubricating oil return, ventilation (make bearing bore internal pressure as far as possible and external environment condition be consistent, thus reduce the charge oil pressure of lubricant oil and engine bearing chamber and to obturage the working stability of system) and detection etc.
Further preferably, the quantity of described center tracheae is 6, is arranged at respectively in 6 described load support plate cavitys.Bearing is the key component in transmission system, and the quality of its performance directly has influence on working life and the reliability of transmission system.Therefore, when only having the center tracheae of a confession bearing oil or oil return, if go wrong when fuel feeding or oil return, then can affect whole transmission system, therefore Liang Gen center tracheae fuel feeding and the tracheae oil return of Liang Gen center are set respectively, when as fuel feeding or oil return wherein a center tracheae goes wrong time, then also have another root center tracheae for subsequent use, ensure that the stability of system.
The present invention has following beneficial effect:
The invention provides a kind of supporting system for gas-turbine unit turbine parts of global optimization; for reaching effective cooling load support plate; and effectively can prevent the object that load support plate splits; the part that ingenious property ground is positioned at high-temperature high-pressure fuel gas at load support plate arranges pneumatic blade profile support plate; make load support plate be positioned at pneumatic blade profile support plate cavity through the part of main duct, pneumatic blade profile support plate plays as the armor effect that protection is arranged in the load support plate of its cavity.Further this pneumatic blade profile support plate is set to aerofoil profile, the unique aerodynamic characteristic utilizing aerofoil profile to have, the load support plate that contraposition play supporting role in chamber in the inner serves good protective action, and the pneumatic blade profile support plate of aerofoil profile is because of the shape facility of itself uniqueness, high-temperature high-pressure fuel gas is relatively little to its damage, as added a protection armor outside load support plate; From load support plate inner chamber, cooled gas out directly can enter pneumatic blade profile support plate; also cooling action is served to pneumatic blade profile support plate; and the load support plate being arranged in pneumatic blade profile support plate inner chamber is not only cooled in outside; and pneumatic blade profile support plate and the gas between pneumatic blade profile support plate and load support plate all serve powerful protective action to it, thus improve the life and reliability of load support plate.Further, the cross section of described load support plate is racetrack, and manufacturing is simple, and bearing capacity is up to standard, and geometric space utilization ratio is large, and can reach required Throughput requirement as required.Further, arrange center tracheae in load support plate inner chamber, be preferably provided with 6 center tracheaes, structure is more compact to be suitable for, and for adding bearing oil, oil return, detection and ventilation, operation is simple.
Overall technical architecture structure optimization of the present invention, simple, solve load support plate well by the scissile problem of high-temperature high-pressure fuel gas, ensure structural life-time and the reliability of load supporting system; It also avoid the rising pursued simply and use the better high-temperature alloy material of temperature resistant capability to prepare the cost that load support plate brings.
Accompanying drawing explanation
The Figure of description forming a application's part is used to provide a further understanding of the present invention, and schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 is preferred embodiment of the present invention structural representation.
Fig. 2 is preferred embodiment of the present invention load supporting system schematic three dimensional views.
Fig. 3 is the pneumatic blade profile support plate of the preferred embodiment of the present invention, load support plate and center tracheae position relationship schematic diagram.
In Fig. 1 ~ 3,1 is bearing support, and 2 is support case, and 3 is load support plate, and 4 is pneumatic blade profile support plate, 5 is by-pass air duct, and 6 is main duct, and 7 is turbine rotor, and 8 is bearing, and 9 is bearing bore, 10 is cooling-air, and 11 is high-temperature fuel gas, and 12 is suction port, and 13 is air outlet, tracheae centered by 14.
Embodiment
Below in conjunction with accompanying drawing, embodiments of the invention are described in detail, but the multitude of different ways that the present invention can be defined by the claims and cover is implemented.
As depicted in figs. 1 and 2, the invention provides a kind of supporting system for gas-turbine unit turbine parts, described supporting system comprises bearing support 1, support case 2 and the coupling shaft bearing 1 multiple load support plates 3 uniform with the circumference of support case 2; Described load support plate 3 is cavity structure, and the part that load support plate 3 is positioned at by-pass air duct 5 has suction port 12, and load support plate 3 has air outlet 13 near bearing support 1 place; The outer installment that described load support plate 3 is positioned at the part of main duct 6 has pneumatic blade profile support plate 4, as shown in Figure 3, described pneumatic blade profile support plate 4 is provided with cavity, and load support plate 3 is positioned at the cavity of pneumatic blade profile support plate 4, pneumatic blade profile support plate 4 has air outlet (not marking in figure).The present invention has pneumatic blade profile support plate 4 at load support plate 3 through the outer installment of the part of main duct 6; make load support plate 3 be positioned at pneumatic blade profile support plate 4 cavity through the part of main duct 6, pneumatic blade profile support plate 4 plays as the armor effect that protection is arranged in the load support plate 3 of its cavity.
As shown in Figure 3, described pneumatic blade profile support plate 4 is the cavity structure of aerofoil profile, and load support plate 3 is positioned at pneumatic blade profile support plate 4 cavity.Pneumatic blade profile support plate 4 is set to aerofoil profile; play the aerodynamic characteristic of its excellent aerodynamics aspect; when air-flow is by aerofoil profile pneumatic blade profile support plate 4; the pressure from air-flow that pneumatic blade profile support plate 4 is subject to is very little, and the pneumatic blade profile support plate 4 of aerofoil profile plays the effect of the load support plate 3 of guard bit in the inner in chamber as the armor.
In described load support plate 3 cavity, center tracheae 14 is set.Described center tracheae 14 is arranged in the cavity of described load support plate 3.In load support plate 3 cavity, the effect that center tracheae 14 plays transmission is set.Load support plate 3 is connected with bearing support 1, and for ensureing the requirement such as the working life of bearing and the stability of system architecture, need lubricate bearing, the present invention adds center tracheae 14, adds lubricant oil to bearing by center tracheae 14; In order to balance the air pressure in load support plate 3, be communicated with barometric pressure by center tracheae 14; Sometimes need to detect back-up system inside, also by center tracheae 14, detection device is inserted.
The cross section of described load support plate 3 is racetrack by the present embodiment.Cross section is that load support plate 3 process for machining and manufacturing of racetrack is simple, and ensure that load support plate 3 bearing capacity is up to standard further, geometric space utilization ratio is large, and can reach required Throughput requirement as required.
The quantity of described central gas 14 pipe is 6, is arranged at respectively in 6 described load support plate 3 cavitys.
The supporting system that the present invention adopts, pneumatic channel be separated with load supporting system, pneumatic blade profile support plate 4 utilizes panel beating or casting to realize pneumatic modelling, forms blast tube with main duct 6; Load support plate 3 passes from pneumatic blade profile support plate 4 inside, is inside and outsidely connected with bearing support 1 and support case 2 respectively.First the cooling-air 10 attracted from engine front enters load support plate 3 inner chamber from load support plate 3 suction port 12 through by-pass air duct 5, enters the cooling that the cavity of sprue (by-pass air duct 5 and main duct 6) between inwall and bearing support 1 realizes load support plate 3 and bearing support 1; Cooling-air 10 enters the Cavity Flow between load support plate 3 gentle movable vane type support plate 4 through load support plate 3 air outlet 13 more afterwards, realize isolating to high-temperature fuel gas 11 and supporting system 3, the air outlet finally again on pneumatic blade profile support plate 4 enters sprue and continues to participate in acting.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included in of the present invention comprising within scope.
Claims (6)
1. the supporting system for gas-turbine unit turbine parts, described supporting system comprises the uniform multiple load support plates of circumference of bearing support, support case and coupling shaft bearing and support case, and described load support plate is through the by-pass air duct of turbine part and main duct; Described load support plate is cavity structure, and the part that load support plate is positioned at by-pass air duct has suction port, and load support plate has air outlet near bearing support place; It is characterized in that, described load support plate has pneumatic blade profile support plate through the outer installment of the part of main duct, described pneumatic blade profile support plate is provided with cavity structure, and described load support plate is positioned at the cavity of pneumatic blade profile support plate through the part of main duct, and pneumatic blade profile support plate has air outlet.
2. according to claim 1 for the supporting system of gas-turbine unit turbine parts, it is characterized in that, described pneumatic blade profile support plate is airfoil structure.
3. according to claim 1 for the supporting system of gas-turbine unit turbine parts, it is characterized in that, the cross section of described load support plate is racetrack.
4. according to claim 1 for the supporting system of gas-turbine unit turbine parts, it is characterized in that, also comprise center tracheae, described center tracheae is positioned at the cavity of described load support plate.
5. according to claim 4 for the supporting system of gas-turbine unit turbine parts, it is characterized in that, the quantity of described center tracheae is 4 ~ 9, and each center tracheae is arranged in the cavity of a described load support plate.
6. according to claim 4 for the supporting system of gas-turbine unit turbine parts, it is characterized in that, the quantity of described center tracheae is 6, is arranged at respectively in the cavity of 6 described load support plates.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510348279.7A CN105003303A (en) | 2015-06-23 | 2015-06-23 | Supporting system for turbine part of gas turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510348279.7A CN105003303A (en) | 2015-06-23 | 2015-06-23 | Supporting system for turbine part of gas turbine engine |
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| Publication Number | Publication Date |
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| CN105003303A true CN105003303A (en) | 2015-10-28 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510348279.7A Pending CN105003303A (en) | 2015-06-23 | 2015-06-23 | Supporting system for turbine part of gas turbine engine |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108104952A (en) * | 2017-12-15 | 2018-06-01 | 中国航发沈阳发动机研究所 | The high temperature support case that a kind of self-loopa efficiently cools down |
| CN110529287A (en) * | 2019-08-13 | 2019-12-03 | 中国航发贵阳发动机设计研究所 | A kind of combination in series punching engine fan splitter |
| CN110761855A (en) * | 2019-10-11 | 2020-02-07 | 中国航发沈阳发动机研究所 | Gas turbine engine rear casing |
| CN112648026A (en) * | 2020-12-16 | 2021-04-13 | 中国航发沈阳发动机研究所 | Intermediary cartridge receiver structure |
| CN113982707A (en) * | 2021-11-04 | 2022-01-28 | 中国航发沈阳黎明航空发动机有限责任公司 | Aeroengine unloading cavity exhaust steering support plate |
| CN115355089A (en) * | 2022-07-29 | 2022-11-18 | 中科航星科技有限公司 | Bearing oil mist lubrication cooling structure with axis oil supply |
| CN117145593A (en) * | 2023-11-01 | 2023-12-01 | 中国航发沈阳发动机研究所 | Interactive air flow path multifunctional rear bearing casing structure |
| CN117569923A (en) * | 2024-01-12 | 2024-02-20 | 成都中科翼能科技有限公司 | Turbine fulcrum structure of gas turbine |
-
2015
- 2015-06-23 CN CN201510348279.7A patent/CN105003303A/en active Pending
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108104952A (en) * | 2017-12-15 | 2018-06-01 | 中国航发沈阳发动机研究所 | The high temperature support case that a kind of self-loopa efficiently cools down |
| CN110529287A (en) * | 2019-08-13 | 2019-12-03 | 中国航发贵阳发动机设计研究所 | A kind of combination in series punching engine fan splitter |
| CN110529287B (en) * | 2019-08-13 | 2022-08-26 | 中国航发贵阳发动机设计研究所 | Shunt casing for tandem type combined stamping engine |
| CN110761855A (en) * | 2019-10-11 | 2020-02-07 | 中国航发沈阳发动机研究所 | Gas turbine engine rear casing |
| CN112648026A (en) * | 2020-12-16 | 2021-04-13 | 中国航发沈阳发动机研究所 | Intermediary cartridge receiver structure |
| CN113982707A (en) * | 2021-11-04 | 2022-01-28 | 中国航发沈阳黎明航空发动机有限责任公司 | Aeroengine unloading cavity exhaust steering support plate |
| CN115355089A (en) * | 2022-07-29 | 2022-11-18 | 中科航星科技有限公司 | Bearing oil mist lubrication cooling structure with axis oil supply |
| CN115355089B (en) * | 2022-07-29 | 2024-08-27 | 中科航星科技股份有限公司 | Bearing oil mist lubrication cooling structure for axial center oil supply |
| CN117145593A (en) * | 2023-11-01 | 2023-12-01 | 中国航发沈阳发动机研究所 | Interactive air flow path multifunctional rear bearing casing structure |
| CN117145593B (en) * | 2023-11-01 | 2024-01-02 | 中国航发沈阳发动机研究所 | Interactive air flow path multifunctional rear bearing casing structure |
| CN117569923A (en) * | 2024-01-12 | 2024-02-20 | 成都中科翼能科技有限公司 | Turbine fulcrum structure of gas turbine |
| CN117569923B (en) * | 2024-01-12 | 2024-04-05 | 成都中科翼能科技有限公司 | Turbine fulcrum structure of gas turbine |
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Application publication date: 20151028 |