阅读说明：本技术 一种新型鼓筒式燃气轮机 (Novel drum type gas turbine ) 是由 夏前锦 连龙 瞿建雄 尹金星 薛原 王永生 于 2020-03-26 设计创作，主要内容包括：本发明公开一种新型鼓筒式燃气轮机,具体涉及燃气轮机领域,包括燃气轮机和台架,所述燃气轮机设于台架上；所述燃气轮机包括内鼓筒和外鼓筒,所述内鼓筒设于外鼓筒内部,所述内鼓筒一端外侧固定设有风扇导叶,所述外鼓筒靠近风扇导叶一端外侧固定设有风扇动叶,所述内鼓筒靠近风扇导叶一端外侧固定设有压气机各级导叶,所述外鼓筒靠近压气机各级导叶一端内侧固定设有压气机各级动叶,所述内鼓筒远离压气机各级导叶一端外侧固定设有涡轮各级导叶,所述外鼓筒靠近涡轮各级导叶一端内侧固定设有涡轮各级动叶。本发明通过使用鼓筒式传动,能够克服目前燃气轮机冷却压力大、内部结构件容易应力集中、整机抗弯扭性能差以及设计难度高等问题。(The invention discloses a novel drum type gas turbine, and particularly relates to the field of gas turbines, wherein the novel drum type gas turbine comprises a gas turbine and a rack, wherein the gas turbine is arranged on the rack; the gas turbine includes interior drum barrel and outer drum barrel, interior drum barrel is located inside the outer drum barrel, the fixed fan stator that is equipped with in interior drum barrel one end outside, outer drum barrel is close to the fixed fan movable vane that is equipped with in fan stator one end outside, interior drum barrel is close to the fixed stator at all levels of compressor in fan stator one end outside, outer drum barrel is close to the inboard fixed movable vane at all levels of compressor of being equipped with in the stator one end at all levels of compressor, interior drum barrel is kept away from the fixed stator at all levels of turbine in the stator one end outside at all levels of compressor, outer drum barrel is close to the inboard fixed movable vane at all levels of turbine of being equipped with. By using drum type transmission, the invention can overcome the problems of large cooling pressure, easy stress concentration of internal structural components, poor bending and torsion resistance of the whole machine, high design difficulty and the like of the conventional gas turbine.)

1. A novel drum type gas turbine is characterized in that: the gas turbine is arranged on the rack;

the gas turbine comprises an inner drum and an outer drum, wherein the inner drum is arranged inside the outer drum, a fan guide vane is fixedly arranged on the outer side of one end of the inner drum, a fan movable vane is fixedly arranged on the outer side of one end, close to the fan guide vane, of the outer drum, each stage of guide vanes of the gas compressor are fixedly arranged on the outer side of one end, close to the fan guide vane, of the inner drum, each stage of movable vanes of the gas compressor are fixedly arranged on the inner side of one end, close to each stage of guide vanes of the gas compressor, of the outer drum, each stage of movable vanes of the gas compressor are fixedly arranged on the outer side of one end, far away from each stage of guide vanes of the gas compressor, of the inner;

the rack comprises a base, an inner drum front positioning seat and an inner drum rear positioning seat are fixedly arranged at the top of the base, and an outer drum front centering and positioning roller assembly and an outer drum rear centering and positioning roller assembly are mounted at the top of the base.

2. The drum-type gas turbine according to claim 1, wherein: the gas turbine comprises a fan section, an axial flow compressor section, a combustion chamber section, a turbine section and a tail injection pipe section.

3. The drum-type gas turbine according to claim 2, wherein: the axial flow compressor section is arranged on one side of the fan section, the combustion chamber section is arranged on one side, away from the fan section, of the axial flow compressor section, the turbine section is arranged on one side, away from the axial flow compressor section, of the combustion chamber section, and the tail spraying pipe section is arranged on one side, away from the combustion chamber section, of the turbine section.

4. The drum-type gas turbine according to claim 1, wherein: the inner drum barrel is fixedly arranged on the inner drum barrel front positioning seat and the inner drum barrel rear positioning seat.

5. The drum-type gas turbine according to claim 1, wherein: the outer drum is arranged on the front centering and positioning roller assembly of the outer drum and the rear centering and positioning roller assembly of the outer drum, and the front centering and positioning roller assembly of the outer drum and the rear centering and positioning roller assembly of the outer drum are matched with the outer drum in a rolling manner through rollers.

6. The drum-type gas turbine according to claim 1, wherein: the outer drum front centering and positioning roller assembly and the outer drum rear centering and positioning roller assembly are arranged between the inner drum front positioning seat and the inner drum rear positioning seat.

7. The drum-type gas turbine according to claim 1, wherein: the guide vanes at each stage of the gas compressor and the movable vanes at each stage of the gas compressor are arranged in a staggered manner, and the guide vanes at each stage of the turbine and the movable vanes at each stage of the turbine are arranged in a staggered manner.

8. The drum-type gas turbine according to claim 1, wherein: the fan guide vane is fixedly arranged on the inner drum front positioning seat, and one end of the inner drum close to the inner drum front positioning seat is fixedly connected with the inner drum front positioning seat through a fan section.

Technical Field

The invention belongs to the technical field of gas turbines, and particularly relates to a novel drum type gas turbine.

Background

The gas turbine is an important energy conversion device, plays a very key role in the fields of national production and national defense and military, and the turbine part of the gas turbine is acted by high-temperature thermal stress, high-speed centrifugal force and high-frequency exciting force, which is a difficult point in the design and manufacture of the gas turbine.

Disclosure of Invention

The invention provides a novel drum type gas turbine, and aims to solve the problems of high cooling pressure, high stress concentration and high design difficulty.

The invention is realized in such a way, and provides the following technical scheme: a novel drum type gas turbine comprises a gas turbine and a rack, wherein the gas turbine is arranged on the rack;

the gas turbine comprises an inner drum and an outer drum, wherein the inner drum is arranged inside the outer drum, a fan guide vane is fixedly arranged on the outer side of one end of the inner drum, a fan movable vane is fixedly arranged on the outer side of one end, close to the fan guide vane, of the outer drum, each stage of guide vanes of the compressor are fixedly arranged on the outer side of one end, close to the fan guide vane, of the inner drum, each stage of movable vanes of the compressor are fixedly arranged on the inner side of one end, close to each stage of guide vanes of the compressor, of the outer drum, each stage of movable vanes of the turbine are fixedly arranged on the outer side of one end, far away from each stage of guide vanes of the compressor, of the inner drum, and a tail spray;

the rack comprises a base, an inner drum front positioning seat and an inner drum rear positioning seat are fixedly arranged at the top of the base, and an outer drum front centering and positioning roller assembly and an outer drum rear centering and positioning roller assembly are mounted at the top of the base.

In a preferred embodiment, the gas turbine includes a fan section, an axial compressor section, a combustor section, a turbine section, and a tailpipe section to facilitate stable operation.

In a preferred embodiment, the axial flow compressor section is disposed on one side of the fan section, the combustor section is disposed on one side of the axial flow compressor section away from the fan section, the turbine section is disposed on one side of the combustor section away from the axial flow compressor section, and the tail pipe section is disposed on one side of the turbine section away from the combustor section, so as to facilitate stable operation.

In a preferred embodiment, the inner drum is fixedly arranged on the inner drum front positioning seat and the inner drum rear positioning seat so as to facilitate the fixation of the inner drum.

In a preferred embodiment, the outer drum is disposed on the outer drum front centering and positioning roller assembly and the outer drum rear centering and positioning roller assembly, and both the outer drum front centering and positioning roller assembly and the outer drum rear centering and positioning roller assembly are in rolling fit with the outer drum through rollers so as to facilitate the rotation of the outer drum.

In a preferred embodiment, the outer drum front centering and positioning roller assembly and the outer drum rear centering and positioning roller assembly are arranged between the inner drum front positioning seat and the inner drum rear positioning seat so as to fixedly position the outer drum and the inner drum.

In a preferred embodiment, the compressor stage guide vanes and the compressor stage movable blades are arranged in a staggered mode, and the turbine stage guide vanes and the turbine stage movable blades are arranged in a staggered mode, so that stable operation is facilitated.

In a preferred embodiment, the fan guide vane is fixedly arranged on the inner drum front positioning seat, and one end of the inner drum close to the inner drum front positioning seat is fixedly connected with the inner drum front positioning seat through a fan section so as to facilitate the fixed positioning of the inner drum.

Compared with the prior art, the invention has the beneficial effects that:

1. by eliminating a complex disc shaft type structure, parts exposed in high-temperature gas only comprise the inner wall of the outer drum, the turbine blades and the outer wall of the inner drum, the number of the high-temperature parts is reduced, the design requirement of alternating thermal stress on engine part assembly in a working-stopping-working circulation state is lowered, and the overall reliability of the gas turbine is improved along with the reduction of the number of the high-temperature parts, so that the reliability of the parts and the service life of the whole gas turbine can be obviously improved.

The drum type gas turbine has the advantages that the number of high-temperature parts is small, the requirement on cooling gas is reduced, and the efficiency of the gas compressor is improved through phase change.

The cooling gas channel can be established without damaging the structure of the components in the cooling gas delivery of the drum type gas turbine, so that the problems of stress concentration or insufficient strength of the components can be effectively avoided.

The drum type gas turbine adopts a drum barrel to transfer force and torque, the stress and the bending torque resistance performance are better than those of a disc shaft structure, the deformation of a rotating part during working is small, in addition, the rotating part only contains the drum barrel and the moving blade, the mass of the rotating part is greatly reduced, and the rotational inertia is small.

The drum type gas turbine air cooling passage is minimally affected by high-temperature gas, the cooling effect can be guaranteed, the lubricating oil system does not pass through a high-temperature gas coverage area, and the cooling problem of the lubricating oil system does not need to be considered.

The drum type gas turbine adopts a hollow structure, the maintenance and flaw detection are convenient, the replacement of parts is relatively simpler, the centering and positioning part is positioned outside the core machine, and the running state of the engine is easy to control.

The rotor part of the drum type gas turbine is arranged outside the engine, and the starter can finish the starting process without entering a flow channel, so that the influence of the starter on a working medium flow channel is avoided.

The drum type gas turbine has less high-temperature rotating parts, and only the outer drum barrel and the turbine movable blades are influenced by the rotating centrifugal force and the thermal stress, so the design difficulty is reduced.

Drawings

Fig. 1 is a schematic view of the overall structure of the present invention.

FIG. 2 is a schematic front view of the gas turbine according to the present invention.

Fig. 3 is a schematic perspective view of the stand according to the present invention.

In the figure: the device comprises a gas turbine 1, a platform 2, a fan section 11, an axial flow compressor section 12, a combustor section 13, a turbine section 14, a tail spray pipe section 15, an inner drum 16, an outer drum 17, a fan guide vane 111, a fan movable vane 112, a compressor guide vane at each stage 121, a compressor movable vane at each stage 122, a turbine guide vane at each stage 141, a turbine movable vane at each stage 142, a tail spray pipe fixing piece 151, a base 21, a 22 inner drum front positioning seat, a 23 outer drum front centering and positioning roller assembly, a 24 outer drum rear centering and positioning roller assembly and a 25 inner drum rear positioning seat.

Detailed Description

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 the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

In the description of the present invention, it is to be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed in a particular orientation, and be operated, and thus, are not to be construed as limiting the present invention. Further, in the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.

Referring to fig. 1 to fig. 3, the present invention provides a technical solution: a novel drum type gas turbine comprises a gas turbine 1 and a rack 2, wherein the gas turbine 1 is arranged on the rack 2;

the gas turbine 1 comprises an inner drum 16 and an outer drum 17, wherein the inner drum 16 is arranged inside the outer drum 17, the outer side of one end of the inner drum 16 is fixedly provided with a fan guide vane 111, the outer side of one end, close to the fan guide vane 111, of the outer drum 17 is fixedly provided with a fan movable vane 112, the outer side of one end, close to the fan guide vane 111, of the inner drum 16 is fixedly provided with a compressor stage guide vane 121, the inner side of one end, close to the compressor stage guide vane 121, of the outer drum 17 is fixedly provided with a compressor stage movable vane 122, the outer side of one end, far away from the compressor stage guide vane 121, of the inner drum 16 is fixedly provided with a turbine stage guide vane 141, the inner side of one end, close to the turbine stage guide vane 141, of the outer drum;

the rack 2 comprises a base 21, the top of the base 21 is fixedly provided with an inner drum front positioning seat 22 and an inner drum rear positioning seat 25, and the top of the base 21 is provided with an outer drum front centering and positioning roller assembly 23 and an outer drum rear centering and positioning roller assembly 24;

the gas turbine 1 comprises a fan section 11, an axial flow compressor section 12, a combustion chamber section 13, a turbine section 14 and a tail injection pipe section 15;

the axial flow compressor section 12 is arranged on one side of the fan section 11, the combustion chamber section 13 is arranged on one side, far away from the fan section 11, of the axial flow compressor section 12, the turbine section 14 is arranged on one side, far away from the axial flow compressor section 12, of the combustion chamber section 13, and the tail gas injection pipe section 15 is arranged on one side, far away from the combustion chamber section 13, of the turbine section 14;

the inner drum 16 is fixedly arranged on the inner drum front positioning seat 22 and the inner drum rear positioning seat 25;

the outer drum 17 is arranged on an outer drum front centering and positioning roller assembly 23 and an outer drum rear centering and positioning roller assembly 24, and the outer drum front centering and positioning roller assembly 23 and the outer drum rear centering and positioning roller assembly 24 are in rolling fit with the outer drum 17 through rollers;

the outer drum front centering and positioning roller assembly 23 and the outer drum rear centering and positioning roller assembly 24 are arranged between the inner drum front positioning seat 22 and the inner drum rear positioning seat 25;

the compressor stage guide vanes 121 and the compressor stage movable vanes 122 are arranged in a staggered manner, and the turbine stage guide vanes 141 and the turbine stage movable vanes 142 are arranged in a staggered manner;

the fan guide vane 111 is fixedly arranged on the inner drum front positioning seat 22, and one end of the inner drum 16 close to the inner drum front positioning seat 22 is fixedly connected with the inner drum front positioning seat 22 through the fan section 11.