CN106762139A - A kind of gas turbine with embedded blade - Google Patents
A kind of gas turbine with embedded blade Download PDFInfo
- Publication number
- CN106762139A CN106762139A CN201710053760.2A CN201710053760A CN106762139A CN 106762139 A CN106762139 A CN 106762139A CN 201710053760 A CN201710053760 A CN 201710053760A CN 106762139 A CN106762139 A CN 106762139A
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- blades
- casing
- turbine
- compressor
- hub
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 24
- 230000003068 static effect Effects 0.000 claims description 18
- 239000000446 fuel Substances 0.000 claims description 9
- 230000009471 action Effects 0.000 claims description 3
- 230000009467 reduction Effects 0.000 description 3
- 230000003247 decreasing effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 108010015780 Viral Core Proteins Proteins 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000306 component Substances 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
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- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides a kind of gas turbine with embedded blade, casing and support cylinder are coaxially disposed, and wheel hub is coaxially disposed inside casing, and wheel hub can rotate relative to casing；The close compressor air inlet machine mouthful side of wheel hub is provided with gas compressor moving blade, gas compressor moving blade correspondence position is provided with compressor stator in casing；The close turbine gas outlet side of wheel hub is provided with turbine rotor blade, turbine rotor blade correspondence position is provided with Turbomachinery in casing；Combustion chamber is toroidal combustion chamber, is fixed on casing periphery.Compressor blade of the invention and turbo blade two ends are fixed, and can stop a leak flowing, improve the efficiency of compressor and turbine；The blade bigger than cantilevered paddle size can be used, compressor single-stage pressure ratio is improve, is improve turbine single-stage capacity for work, and alleviate the weight of blade；Improve the performance of compressor and turbine.
Description
Technical Field
The invention relates to the technical field of propellers, in particular to a gas turbine with embedded blades.
Background
Gas turbines are widely used in aviation and power industries. The industrial gas turbine requires high efficiency and stable and safe operation; the aviation gas turbine is used as the heart of the airplane and plays an important role in the development process of the airplane, and the technical and tactical indexes of the modern airplane are continuously improved, so that higher requirements are provided for the aeroengine: the engine is required to have high thrust-weight ratio, high efficiency, large flow, low fuel consumption and wide stable working range. The compressor and the turbine are two major core components of the gas turbine, and the traditional design modes comprise an axial flow mode and a centrifugal mode. The axial-flow compressor has the advantages of large flow and small single-stage pressure ratio, so that the pressure ratio is improved by adopting a multi-stage axial-flow compressor design, and the adverse effects of high manufacturing cost, complex structure and device weight are caused; the centrifugal compressor has the advantages of high single-stage pressure ratio and small flow area and flow rate. Therefore, the defects of the traditional compressor are urgently needed to be overcome in the field, and the new requirements of the modern gas turbine are met.
Disclosure of Invention
Technical problem to be solved
In view of the above, the present invention provides a gas turbine with embedded blades, in which the compressor single-stage pressure ratio is high, the turbine single-stage work capacity is large, and the overall efficiency is high.
(II) technical scheme
The present invention provides a gas turbine with embedded blades, comprising: a casing assembly, a hub and a combustion chamber; wherein, the receiver subassembly includes: the casing and the supporting cylinder are coaxially arranged; the hub is coaxially arranged in the casing and can rotate relative to the casing; the side, close to the air inlet of the air compressor, of the hub is provided with air compressor movable blades, and the positions, corresponding to the air compressor movable blades, of the casing are provided with air compressor stationary blades; a turbine movable blade is arranged on one side, close to a turbine air outlet, of the hub, and a turbine stationary blade is arranged at a position, corresponding to the turbine movable blade, of the casing; the combustion chamber is an annular combustion chamber and is fixed on the periphery of the casing; air enters from the air inlet of the air compressor and then is turned into radial flow, the hub drives the movable blades of the air compressor to rotate, the air flowing in the radial direction is decelerated and expanded under the action of the movable blades of the air compressor and the fixed blades of the air compressor, enters the combustion chamber and is mixed and combusted with fuel to generate high-temperature and high-pressure gas, the high-temperature and high-pressure gas flows through the fixed blades and the movable blades of the turbine to accelerate and do work, the movable blades of the turbine are pushed to rotate and drive the hub to rotate, and the high-temperature.
Preferably, the compressor movable blade and the compressor stationary blade are both embedded blades.
Preferably, the compressor moving blade comprises a plurality of moving blades which are uniformly arranged along the circumferential direction of the hub, and the compressor stationary blade comprises a plurality of stationary blades which are uniformly arranged along the circumferential direction of the casing; the moving blades and the static blades are respectively embedded into the hub and the casing, two ends of the moving blades are fixed with the hub, and two ends of the static blades are fixed with the casing.
Preferably, the number of moving blades and vanes is the same.
Preferably, the turbine blades and vanes are embedded blades.
Preferably, the turbine blade comprises a plurality of blades which are uniformly arranged along the circumferential direction of the hub, and the turbine stator blade comprises a plurality of stator blades which are uniformly arranged along the circumferential direction of the casing; the moving blades and the static blades are respectively embedded into the hub and the casing, two ends of the moving blades are fixed with the hub, and two ends of the static blades are fixed with the casing.
Preferably, the number of moving blades and vanes is the same.
Preferably, the inlet end and the outlet end of the casing each have a set of casing support rods for supporting the casing and the support cylinder, each set of casing support rods comprising a plurality of radially extending support rods.
Preferably, the air inlet end and the air outlet end of the hub are each provided with a bearing by which the hub is rotatable relative to the casing.
Preferably, the combustor comprises a combustor inlet, a combustor outlet and a plurality of fuel tubes inserted into the combustor; the inlet of the combustion chamber corresponds to the positions of the compressor movable blades and the compressor static blades, and the outlet of the combustion chamber corresponds to the positions of the turbine movable blades and the turbine static blades.
(III) advantageous effects
According to the technical scheme, the gas turbine with the embedded blades has the following beneficial effects:
(1) in the passage formed by the compressor blades and the compressor vanes, the gas flows in a direction of increasing the radius in the radial direction, and in the passage formed by the turbine blades and the turbine vanes, the gas flows in a direction of decreasing the radius in the radial direction. The circumferential section area is increased along the radius increasing direction, so that the gas is decelerated and diffused; on the contrary, along the direction of radius reduction, the circumferential section area is reduced, so that the gas is accelerated to do work, and compared with an axial-flow type compressor, the axial-flow type compressor has the advantages of high single-stage pressure ratio, simple structure, small volume, light weight and low cost; compared with a centrifugal compressor, the centrifugal compressor has the advantages that the flow area is large, the flow is large, and therefore the performances of the compressor and a turbine are improved;
(2) both ends of the compressor blade and the turbine blade are fixed, so that leakage flow can be eliminated, and the efficiency of the compressor and the turbine is improved;
(3) the two ends of the compressor blade and the turbine blade are fixed, so that the stress distribution on the blade is improved, the blade with the size larger than that of the cantilever type blade can be adopted, the single-stage pressure ratio of the compressor is improved, the single-stage work capacity of the turbine is improved, and the weight of the blade is reduced.
Drawings
FIG. 1 is a three-dimensional schematic view of a gas turbine engine having an embedded blade according to an embodiment of the present invention;
FIG. 2 is a schematic half-section view of a gas turbine engine having an embedded blade according to an embodiment of the present invention;
FIG. 3 is a three-dimensional schematic view of FIG. 1 with the combustion chamber omitted;
FIG. 4 is a schematic view of the airflow direction of a gas turbine with embedded blades according to an embodiment of the present invention.
Description of the symbols
1-moving blades of a compressor; 2-a compressor stator blade; 3-turbine rotor blades; 4-a turbine stator blade; 5-a combustion chamber; 6-combustion chamber inlet; 7-a combustion chamber outlet; 8-a hub; 9-a casing; 10-a support cylinder; 11-compressor inlet; 12-case support bar; 13-a bearing; 14-turbine outlet; 15-fuel line; 16-bearing support bar.
Detailed Description
The invention provides a gas turbine with embedded blades, wherein a gas compressor of the gas turbine adopts axial gas inlet and radial flow pressurization; the turbine adopts a pneumatic layout mode of radial flow work and axial exhaust; the combustion chamber is of an annular structure and is arranged at the periphery of the casing. The two ends of the embedded blades of the gas turbine are fixed, so that the strength of the blades can be increased, the blades with larger sizes can be adopted, the single-stage pressure ratio of the gas compressor is high, the single-stage work capacity of the turbine is high, and the efficiency of the whole turbine is high.
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further detail below with reference to specific embodiments and the accompanying drawings.
An embodiment of the present invention provides a gas turbine with embedded blades, which integrates a compressor, a combustor, and a turbine, and includes: the casing assembly, hub 8 and combustion chamber 5; wherein,
the receiver subassembly includes: a casing 9, a support cylinder 10 and a casing support rod 12. The supporting cylinder 10 is of a hollow structure, an airflow channel is formed in the supporting cylinder, the casing 9 and the supporting cylinder 10 are coaxially arranged, a set of casing supporting rods 12 are respectively arranged at the air inlet end and the air outlet end of the casing 9 to fixedly support the casing 9 and the supporting cylinder 10, each set of casing supporting rods 12 comprises a plurality of supporting rods extending along the radial direction, one end of each supporting rod is connected with the inner wall of the casing 9, and the other end of each supporting rod is connected with the outer wall of the supporting cylinder 10.
The hub 8 is coaxially arranged inside the casing 9, a bearing 13 is respectively arranged at the air inlet end and the air outlet end of the hub 8, the outer periphery of the bearing 13 is fixed on the inner wall of the casing 9, the inner periphery of the bearing 13 is fixed on the supporting cylinder 10 through a bearing supporting rod 16, and the hub 8 can rotate relative to the casing 9 through the bearing 13.
An annular disc body and a circular disc body are arranged on one side of the supporting cylinder, close to the air compressor air inlet 11, and closer to the middle point of the axis of the supporting cylinder than the bearing supporting rod 16, the annular disc body and the circular disc body are arranged in parallel and perpendicular to the axis of the supporting cylinder 10, an air flow cavity is formed between the annular disc body and the circular disc body, and the annular disc body and the circular disc body are communicated with the air compressor air inlet 11 of the supporting cylinder through an air flow.
The air compressor movable blades 1 are arranged at the positions, corresponding to the airflow cavity, of the hub, the air compressor stationary blades 2 are arranged at the positions, corresponding to the airflow cavity, of the casing, the air compressor movable blades 1 comprise a plurality of movable blades which are uniformly arranged along the circumferential direction of the hub 8, and the air compressor stationary blades 2 comprise a plurality of stationary blades which are uniformly arranged along the circumferential direction of the casing 9. The compressor movable blades 1 and the compressor static blades 2 are both embedded blades, namely, the movable blades and the static blades are respectively embedded into a hub 8 and a casing 9, both ends of the movable blades are fixed with the hub 8, both ends of the static blades are fixed with the casing 9, channels are formed between the adjacent movable blades and between the adjacent static blades, the number of the movable blades and the number of the static blades can be set according to the situation, and the movable blades and the static blades can be the same or different.
The turbine rotor blade 3 is provided on the side of the hub closer to the turbine outlet 14 and closer to the center point of the axis thereof than the bearing support rod 16, the turbine stator blade 4 is provided on the casing at a position corresponding to the turbine rotor blade, the turbine rotor blade 3 includes a plurality of rotor blades arranged uniformly in the circumferential direction of the hub 8, and the turbine stator blade 4 includes a plurality of stator blades arranged uniformly in the circumferential direction of the casing 9. The turbine movable blades 3 and the turbine stationary blades 4 are both embedded blades, that is, the movable blades and the stationary blades are respectively embedded into the hub 8 and the casing 9, both ends of the movable blades are fixed with the hub 8, both ends of the stationary blades are fixed with the casing 9, channels are formed between the adjacent movable blades and between the adjacent stationary blades, the number of the movable blades and the number of the passing blades can be set according to the situation, and the movable blades and the passing blades can be the same or different.
The combustor 5 is an annular combustor fixed to the outer periphery of the casing 9, the combustor inlet 6 corresponds to the compressor blades 1 and compressor vanes 2, and the combustor outlet 7 corresponds to the turbine blades 3 and turbine vanes 4, and includes a plurality of fuel pipes 15 inserted into the combustor 5.
In the gas turbine with embedded blades, air enters the gas turbine from the air compressor air inlet 11 and flows into the airflow cavity along the axial direction through the airflow channel inside the supporting cylinder 10, the air flow is turned into radial flow in the air flow cavity and flows to the compressor movable blades 1, the hub 8 drives the compressor movable blades 1 to rotate, the air flowing in the radial direction continues to flow in the radial direction under the action of the compressor movable blades 1, the air flows through the compressor stationary blades 2 and then is subjected to speed reduction and pressure expansion to form high-pressure air, and enters the combustion chamber 5 from the combustion chamber inlet 6, the fuel enters the combustion chamber 5 from the fuel pipe 15 to be mixed with high-pressure air and then is combusted to generate high-temperature and high-pressure gas, the high-temperature and high-pressure gas is discharged from the combustion chamber outlet 7 and then sequentially flows through the turbine stationary blade 4 and the turbine movable blade 3 to do work by increasing the speed, so as to push the turbine movable blade 3 to rotate, and drives the hub 8 to rotate, and the gas after acting is converted into axial flow and is discharged from a turbine gas outlet 14.
In the gas turbine with the embedded blades of the present invention, the gas flows in the radial direction increasing direction in the passage formed by the compressor rotor blades and the compressor stator blades, and the gas flows in the radial direction decreasing direction in the passage formed by the turbine rotor blades and the turbine stator blades. The compressor and the turbine adopt the pneumatic layout, and the pneumatic layout has the advantages that: the circumferential section area is increased along the radius increasing direction, so that the gas is decelerated and diffused; on the contrary, along the direction of radius reduction, the circumferential section area is reduced, so that the gas is accelerated to do work, and compared with an axial-flow type compressor, the axial-flow type compressor has the advantages of high single-stage pressure ratio, simple structure, small volume, light weight and low cost; compared with a centrifugal compressor, the centrifugal compressor has the advantages of large flow area and large flow, so that the performances of the compressor and the turbine are improved.
Further, in the conventional compressor and turbine, the blades of the compressor and the turbine, whether in an axial flow form or a centrifugal form, are all cantilever type blades, that is, only one end of each blade is fixed on a casing or a hub (wheel disc), and the other end of each blade, which is not fixed, has leakage flow, so that the flow loss is increased. The two ends of the compressor blade and the turbine blade are fixed, so that leakage flow can be eliminated, and the efficiency is improved. Traditional cantilever type blade, the stress that blade root received is very big, in order to prevent blade root fracture, the blade size can not be too big on the one hand, and on the other hand will increase blade root thickness, the disadvantage of bringing like this is: the compressor has small single-stage pressure ratio and small single-stage work capacity of the turbine, and the weight of the blade is also increased. Because the two ends of the compressor blade and the turbine blade of the invention are fixed, the stress distribution on the blade is improved, the blade with larger size than the cantilever type blade can be adopted, the single-stage pressure ratio of the compressor is improved, the single-stage work capacity of the turbine is improved, and the weight of the blade is reduced.
In the present invention, the casing 9 can be fixed, only the hub 8 rotating with respect to the casing 9; in order to increase the pressurizing capacity of the compressor, the casing 9 can be not fixed, and the casing 9 and the hub 8 rotate in opposite directions, so that the fixed blades of the compressor can be driven to rotate, the counter-rotation of the movable blades and the fixed blades of the compressor is formed, the pressurizing capacity of the compressor is increased, and the efficiency of the compressor is improved.
It is to be noted that, in the attached drawings or in the description, the implementation modes not shown or described are all the modes known by the ordinary skilled person in the field of technology, and are not described in detail. In addition, the above definitions of the components are not limited to the specific structures and shapes mentioned in the embodiments, and those skilled in the art may easily modify or replace them, for example:
(1) examples of parameters that include particular values may be provided herein, but the parameters need not be exactly equal to the corresponding values, but may be approximated to the corresponding values within acceptable error tolerances or design constraints;
(2) directional phrases used in the embodiments, such as "upper", "lower", "front", "rear", "left", "right", etc., refer only to the orientation of the attached drawings and are not intended to limit the scope of the present invention;
(3) the embodiments described above may be mixed and matched with each other or with other embodiments based on design and reliability considerations, i.e. technical features in different embodiments may be freely combined to form further embodiments.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the present invention, and any modifications, equivalents, improvements and the like made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A gas turbine engine having an embedded blade, comprising: a casing assembly, a hub and a combustion chamber; wherein,
the receiver subassembly includes: the casing and the supporting cylinder are coaxially arranged;
the hub is coaxially arranged in the casing and can rotate relative to the casing;
the side, close to the air inlet of the air compressor, of the hub is provided with air compressor movable blades, and the positions, corresponding to the air compressor movable blades, of the casing are provided with air compressor stationary blades;
a turbine movable blade is arranged on one side, close to a turbine air outlet, of the hub, and a turbine stationary blade is arranged at a position, corresponding to the turbine movable blade, of the casing;
the combustion chamber is an annular combustion chamber and is fixed on the periphery of the casing;
air enters from the air inlet of the air compressor and then is turned into radial flow, the hub drives the movable blades of the air compressor to rotate, the air flowing in the radial direction is decelerated and expanded under the action of the movable blades of the air compressor and the fixed blades of the air compressor, enters the combustion chamber and is mixed and combusted with fuel to generate high-temperature and high-pressure gas, the high-temperature and high-pressure gas flows through the fixed blades and the movable blades of the turbine to accelerate and do work, the movable blades of the turbine are pushed to rotate and drive the hub to rotate, and the high-temperature.
2. The gas turbine of claim 1,
the movable blades and the fixed blades of the compressor are embedded blades.
3. The gas turbine according to claim 2,
the compressor movable blades comprise a plurality of movable blades which are uniformly arranged along the circumferential direction of the hub, and the compressor fixed blades comprise a plurality of fixed blades which are uniformly arranged along the circumferential direction of the casing; the moving blades and the static blades are respectively embedded into the hub and the casing, two ends of the moving blades are fixed with the hub, and two ends of the static blades are fixed with the casing.
4. The gas turbine according to claim 3,
the number of the moving blades and the moving blades is the same.
5. The gas turbine of claim 1,
the turbine movable blades and the turbine fixed blades are embedded blades.
6. The gas turbine according to claim 5,
the turbine movable blades comprise a plurality of movable blades which are uniformly arranged along the circumferential direction of the hub, and the turbine fixed blades comprise a plurality of fixed blades which are uniformly arranged along the circumferential direction of the casing; the moving blades and the static blades are respectively embedded into the hub and the casing, two ends of the moving blades are fixed with the hub, and two ends of the static blades are fixed with the casing.
7. The gas turbine of claim 6,
the number of the moving blades and the moving blades is the same.
8. The gas turbine of claim 1,
the air inlet end and the air outlet end of the casing are respectively provided with a group of casing supporting rods for supporting the casing and the supporting cylinder, and each group of casing supporting rods comprises a plurality of supporting rods extending along the radial direction.
9. The gas turbine of claim 1,
the air inlet end and the air outlet end of the hub are respectively provided with a bearing, and the hub can rotate relative to the casing through the bearings.
10. The gas turbine of claim 1, wherein the combustor comprises a combustor inlet, a combustor outlet, and a plurality of fuel tubes inserted into the combustor;
the inlet of the combustion chamber corresponds to the positions of the compressor movable blades and the compressor static blades, and the outlet of the combustion chamber corresponds to the positions of the turbine movable blades and the turbine static blades.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710053760.2A CN106762139B (en) | 2017-01-22 | 2017-01-22 | A kind of gas turbine with embedded blade |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201710053760.2A CN106762139B (en) | 2017-01-22 | 2017-01-22 | A kind of gas turbine with embedded blade |
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| CN106762139A true CN106762139A (en) | 2017-05-31 |
| CN106762139B CN106762139B (en) | 2018-09-04 |
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| CN201710053760.2A Active CN106762139B (en) | 2017-01-22 | 2017-01-22 | A kind of gas turbine with embedded blade |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108868893A (en) * | 2018-01-12 | 2018-11-23 | 至玥腾风科技投资集团有限公司 | A kind of rotor-support-foundation system and its control method and Gas Turbine Generating Units and its control method |
| CN112324520A (en) * | 2020-10-27 | 2021-02-05 | 中国船舶重工集团公司第七0三研究所 | Stationary blade ring structure of gas turbine |
| CN113217114A (en) * | 2021-05-31 | 2021-08-06 | 张龙 | Closed rotary type annular vortex-spraying steam wheel |
| CN113700676A (en) * | 2021-07-27 | 2021-11-26 | 中国科学院工程热物理研究所 | Self-air-entraining control gas turbine compressor guide vane adjusting and driving mechanism |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108868893A (en) * | 2018-01-12 | 2018-11-23 | 至玥腾风科技投资集团有限公司 | A kind of rotor-support-foundation system and its control method and Gas Turbine Generating Units and its control method |
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| CN112324520A (en) * | 2020-10-27 | 2021-02-05 | 中国船舶重工集团公司第七0三研究所 | Stationary blade ring structure of gas turbine |
| CN113217114A (en) * | 2021-05-31 | 2021-08-06 | 张龙 | Closed rotary type annular vortex-spraying steam wheel |
| CN113700676A (en) * | 2021-07-27 | 2021-11-26 | 中国科学院工程热物理研究所 | Self-air-entraining control gas turbine compressor guide vane adjusting and driving mechanism |
| CN113700676B (en) * | 2021-07-27 | 2023-05-16 | 中国科学院工程热物理研究所 | Self-bleed air control guide vane adjusting driving mechanism of gas turbine compressor |
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| CN106762139B (en) | 2018-09-04 |
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