CN219061772U

CN219061772U - Gas turbine blade

Info

Publication number: CN219061772U
Application number: CN202223351379.XU
Authority: CN
Inventors: 田培森
Original assignee: Xi'an Zhongjiefei Industry And Trade Co ltd
Current assignee: Xi'an Zhongjiefei Industry And Trade Co ltd
Priority date: 2022-12-14
Filing date: 2022-12-14
Publication date: 2023-05-23
Anticipated expiration: 2032-12-14

Abstract

The utility model discloses a gas turbine blade, which comprises a main shaft rod, and a cold air zone blade and a hot air zone blade which are arranged outside the main shaft rod, wherein the cold air inlet zone, a combustion heating zone and a hot air exhaust zone are sequentially arranged outside the main shaft rod along the axial direction of the main shaft rod from left to right, the cold air zone blade and the hot air zone blade are respectively arranged at the cold air inlet zone and the hot air exhaust zone, the main shaft rod, the cold air zone blade and the hot air zone blade are of hollow structures, and cooling liquid is filled in the hollow parts of the main shaft rod. According to the utility model, the cooling liquid is circulated between the cold air inlet area and the hot air outlet area through the arrangement of the circulation mechanism, the cooling liquid is cooled in the cold air inlet area, and the cooling liquid flows into the hot air area blades to exchange heat with the hot air area blades through the hollow structures in the hot air area blades, so that the heat dissipation effect of the hot air area blades and the heat dissipation uniformity are ensured, and the heat dissipation effect of the traditional gas turbine blades is improved.

Description

Gas turbine blade

Technical Field

The utility model relates to the technical field of gas turbines, in particular to a gas turbine blade.

Background

The gas turbine is an internal combustion power machine which uses continuously flowing gas as working medium to drive the impeller to rotate at high speed and convert the energy of fuel into useful work, and is a rotary impeller type heat engine.

The air flow channel of the gas turbine is roughly divided into a cold air inlet area, a combustion heating area and a hot exhaust area, wherein the cold air inlet area is used for entering external air, the combustion heating area is used for heating and working for a combustion chamber, the hot exhaust area is used for discharging exhaust gas generated by the combustion chamber in the combustion heating area outwards, and due to the fact that the temperature of the exhaust gas discharged by the hot exhaust area is higher, blades in the exhaust area can be caused to be obviously increased under the action of high temperature under the action of the blade body and the top heat load of the blades, and the blades are easy to oxidize and creep damage. Therefore, in order to ensure the normal and reliable operation of the blade, the blade needs to be effectively cooled, and most of traditional blade cooling adopts a mode of arranging an airflow channel on the blade, and the like, so that although a certain heat dissipation effect can be achieved, the heat dissipation effect is still to be improved.

Disclosure of Invention

The utility model aims at: in order to solve the problem that the heat dissipation effect of the traditional gas turbine blade needs to be improved, a gas turbine blade is provided.

In order to achieve the above purpose, the present utility model adopts the following technical scheme:

the utility model provides a gas turbine blade, includes the main shaft pole and installs at the outside cold wind district blade and hot air district blade of main shaft pole, main shaft pole outside is left to right in proper order along its axial and is cold wind intake zone, burning heating zone and hot exhaust district, cold wind district blade with hot air district blade installs respectively cold wind intake zone with hot exhaust district department, the main shaft pole the cold wind district blade with hot air district blade all is hollow structure, and its inside cavity department is filled with the coolant liquid, and cold wind district blade with the inside of hot air district blade with the inside intercommunication of main shaft pole, install on the main shaft pole and be used for the drive the coolant liquid cold wind intake zone with the circulation mechanism of circulation between the hot exhaust district.

As a further description of the above technical solution:

the circulating mechanism comprises a pump fixed at one end of the main shaft rod far away from the hot exhaust area, and the pump guides the cooling liquid inside the main shaft rod at one side close to the hot exhaust area to the cold air inlet area.

As a further description of the above technical solution:

the inside coaxial fixedly connected with of main shaft pole is inside hollow structure's interior pole, interior pole with main shaft pole inner chamber is isometric, interior pole be close to hot exhaust district one side with the intercommunication of the inside of main shaft pole, interior pole be close to one side and the pump machine intercommunication of cold wind air intake district.

As a further description of the above technical solution:

the cold air zone blades and the hot air zone blades comprise a plurality of groups distributed in an annular array, communicating pipes positioned at the outer edges of the cold air zone blades and the hot air zone blades are communicated with each other, the rightmost group of cold air zone blades are communicated with the inside of the main shaft rod through a flow guide pipe, and the rightmost group of hot air zone blades are communicated with one side, close to the hot exhaust zone, of the inner shaft rod through a return pipe.

As a further description of the above technical solution:

the guide pipe is parallel to the spindle shaft along one end reaching the inside of the spindle shaft, and the opening of the guide pipe faces the hot exhaust area.

In summary, due to the adoption of the technical scheme, the beneficial effects of the utility model are as follows:

through circulation mechanism's setting, with the coolant liquid in cold wind air inlet zone and hot exhaust district between the circulation, through coolant liquid in cold wind air inlet zone cooling, through the inside hollow structure of cold wind district blade, and its inside hollow communicates with the main shaft pole is inside, thereby make the coolant liquid can flow to cold wind district blade inside, increase the radiating area of coolant liquid in cold wind air inlet zone, ensure the cooling effect of coolant liquid, the back flows to hot exhaust district after the coolant liquid cooling, through the inside hollow structure of hot wind district blade, thereby the coolant liquid flows to hot wind district blade inside rather than carrying out the heat exchange, the effect to hot wind district blade radiating and radiating homogeneity have been ensured, traditional gas turbine blade radiating effect has been improved.

Drawings

Fig. 1 shows a schematic perspective view of a structure according to the present utility model;

fig. 2 shows a schematic cross-sectional structure of an outer shaft according to the utility model;

FIG. 3 shows a schematic diagram of a front view structure according to the present utility model;

legend description:

1. a main shaft lever; 2. a pump machine; 3. a cold air zone blade; 4. hot air zone blades; 5. a flow guiding pipe; 6. a return pipe; 7. an inner shaft; 8. and communicating pipe.

Detailed Description

The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.

Referring to fig. 1-3, the present utility model provides a technical solution: the utility model provides a gas turbine blade, including main axostylus axostyle 1 and install at the outside cold wind district blade 3 of main axostylus axostyle 1 and hot wind district blade 4, main axostylus axostyle 1 outside is cold wind intake zone, burning heating zone and hot exhaust district from left to right in proper order along its axial, cold wind district blade 3 and hot wind district blade 4 are installed respectively in cold wind intake zone and hot exhaust district department, main axostylus axostyle 1, cold wind district blade 3 and hot wind district blade 4 all are hollow structure, and its inside cavity department is filled with the coolant liquid, and the inside of cold wind district blade 3 and hot wind district blade 4 communicates with the inside of main axostylus axostyle 1, install the circulation mechanism that is used for driving the coolant liquid and circulate between cold wind intake zone and hot exhaust district on the main axostylus axostyle 1.

The cold air intake zone, the combustion heating zone and the hot exhaust zone are respectively indicated as A, B, C in fig. 3, cooling liquid circulates between the cold air intake zone and the hot exhaust zone through the arrangement of the circulating mechanism, is cooled in the cold air intake zone through the cooling liquid, passes through the hollow structure inside the cold air zone blade 3, and the hollow inside the cold air zone blade 3 is communicated with the inside of the spindle rod 1, so that the cooling liquid can flow into the cold air zone blade 3, the heat dissipation area of the cooling liquid in the cold air intake zone is increased, the cooling effect of the cooling liquid is guaranteed, the cooling liquid flows back to the hot exhaust zone after cooling, and is cooled through the hollow structure inside the hot air zone blade 4, so that the cooling liquid flows into the hot air zone blade 4 to exchange heat with the cooling liquid, and the heat dissipation effect and the heat dissipation uniformity of the hot air zone blade 4 are guaranteed.

Specifically, as shown in fig. 1, the circulation mechanism includes a pump 2 fixed at one end of the main shaft rod 1 far away from the hot air exhaust area, and the pump 2 guides the cooling liquid inside the main shaft rod 1 near one side of the hot air exhaust area to the cold air intake area.

The circulating mode is realized through the pump 2, so that stable circulating power is provided, and the circulating effect is ensured.

Specifically, as shown in fig. 1, an inner shaft rod 7 with an internal hollow structure is coaxially and fixedly connected inside the main shaft rod 1, the inner shaft rod 7 is equal in length with the inner cavity of the main shaft rod 1, one side, close to a hot exhaust area, of the inner shaft rod 7 is communicated with the inside of the main shaft rod 1, one side, close to a cold air inlet area, of the inner shaft rod 7 is communicated with the pump 2, the cold air area blades 3 and the hot air area blades 4 respectively comprise a plurality of groups distributed in an annular array, communicating pipes 8 positioned at the outer edges of the cold air area blades 3 and the hot air area blades 4 are respectively communicated with each other, the right cold air area blades 3 are communicated with the inside of the main shaft rod 1 through a flow guide pipe 5, the right hot air area blades 4 are communicated with one side, close to the hot exhaust area, of the inner shaft rod 7 through a return pipe 6, one end, close to the inside the main shaft rod 1, of the flow guide pipe 5 is parallel to the axis of the main shaft rod 1, and the opening of the flow guide pipe 5 faces the hot exhaust area.

Through all communicate communicating pipe 8 that is located its outer edge department between every group cold wind district blade 3 and every group hot air district blade 4 for after the coolant liquid is thrown to its outer edge department under centrifugal force effect, communicate each other through communicating pipe 8 again, a group of cold wind district blade 3 on the extreme right communicates with the inside of spindle pole 1 through honeycomb duct 5, simultaneously, honeycomb duct 5 is parallel with spindle pole 1 axle center along the one end to spindle pole 1 inside, and the opening part of honeycomb duct 5 is towards hot exhaust district, make the coolant liquid at honeycomb duct 5 end can flow to hot exhaust district under the negative pressure effect that is close to hot exhaust district, in practical implementation, the accessible increases honeycomb duct 5 end and occupies the duty ratio of spindle pole 1 inside cross-section, the negative pressure effort of honeycomb duct 5 opening part is increased, guarantee coolant liquid stability circulation to hot exhaust district, again because a group of the hot air district blade 4 on the extreme right is through back flow duct 6 and inner spindle pole 7 are close to hot exhaust district one side intercommunication, make the negative pressure effort steady action of pump 2 in the end of back flow duct 6, thereby guarantee that the coolant liquid circulates back to hot air district in district blade 4 inside, guarantee that the cooling liquid has guaranteed cooling liquid uniformity and heat dissipation effect of cold wind district blade 4.

The foregoing is only a preferred embodiment of the present utility model, but the scope of the present utility model is not limited thereto, and any person skilled in the art, who is within the scope of the present utility model, should make equivalent substitutions or modifications according to the technical scheme of the present utility model and the inventive concept thereof, and should be covered by the scope of the present utility model.

Claims

1. The utility model provides a gas turbine blade, includes main axostylus axostyle (1) and installs cold wind district blade (3) and hot air district blade (4) outside main axostylus axostyle (1), its characterized in that, main axostylus axostyle (1) outside is prolonged its axial and is left to right cold wind intake zone, burning zone and hot exhaust district in proper order, cold wind district blade (3) with hot air district blade (4) are installed respectively cold wind intake zone with hot exhaust district department, main axostylus axostyle (1) cold wind district blade (3) with hot air district blade (4) all are hollow structure, and its inside cavity department is filled with the coolant liquid, and cold wind district blade (3) with the inside of hot air district blade (4) communicates with the inside of main axostylus axostyle (1), install on main axostylus axostyle (1) and be used for the drive the coolant liquid is in cold wind intake zone with hot exhaust district between endless circulation mechanism.

2. A gas turbine blade according to claim 1, wherein the circulation mechanism comprises a pump (2) fixed at an end of the main shaft (1) remote from the hot exhaust zone, the pump (2) guiding the cooling liquid inside the main shaft (1) near the hot exhaust zone to the cold air intake zone.

3. A gas turbine blade according to claim 1, characterized in that an inner shaft rod (7) with a hollow structure is coaxially and fixedly connected inside the main shaft rod (1), the inner shaft rod (7) is equal in length with an inner cavity of the main shaft rod (1), one side, close to the hot exhaust area, of the inner shaft rod (7) is communicated with the inside of the main shaft rod (1), and one side, close to the cold air inlet area, of the inner shaft rod (7) is communicated with the pump (2).

4. A gas turbine blade according to claim 3, wherein the cold air zone blades (3) and the hot air zone blades (4) each comprise a plurality of groups distributed in a ring array, communicating pipes (8) positioned at the outer edges of the cold air zone blades (3) and the hot air zone blades (4) are communicated with each other, the rightmost group of cold air zone blades (3) are communicated with the inside of the main shaft (1) through the flow guide pipe (5), and the rightmost group of hot air zone blades (4) are communicated with one side, close to the hot exhaust zone, of the inner shaft (7) through a return pipe (6).

5. A gas turbine blade according to claim 4, wherein the flow guide tube (5) is parallel to the axis of the main shaft (1) along an end to the inside of the main shaft (1), and the opening of the flow guide tube (5) is directed towards the hot exhaust zone.