阅读说明：本技术 一种燃气轮机轴承腔用机械非接触式端面密封系统 (Mechanical non-contact end face sealing system for gas turbine bearing cavity ) 是由 刘云宁 刘冰冰 李冬 初曙光 邓庆锋 金鹏 王�琦 王廷 于 2019-12-12 设计创作，主要内容包括：一种燃气轮机轴承腔用机械非接触式端面密封系统,本发明涉及一种密封系统,本发明为解决现有燃气轮机轴承腔使用弹簧橡胶圈进行密封,易造成而造成密封系统失效,导致滑油及其油气被大量地吸入到主流路中,影响叶片的工作特性,以及造成燃烧室燃烧条件恶化和产生积碳的问题,它包括密封环、石墨环和保持环；密封环、石墨环和保持环均为环形体,密封环的一个端面沿径向加工有多个动力槽,保持环上加工有安装槽,密封环上加工有多个动力槽的端面靠近石墨环的一个端面设置,密封环和石墨环安装在保持环的安装槽内,密封环、石墨环和保持环同轴设置,石墨环的另一个端面与安装槽之间设有间隙,间隙的距离为L,本发明用于燃气轮机轴承腔密封时使用。(The invention relates to a mechanical non-contact end face sealing system for a gas turbine bearing cavity, which relates to a sealing system and aims to solve the problems that the sealing system is easy to lose effectiveness due to the fact that the existing gas turbine bearing cavity is sealed by a spring rubber ring, lubricating oil and oil gas thereof are greatly sucked into a main flow path, the working characteristics of blades are influenced, the combustion condition of a combustion chamber is worsened, and carbon deposition is generated; the sealing ring, the graphite ring and the retaining ring are annular bodies, one end face of the sealing ring is provided with a plurality of power grooves along the radial direction, the retaining ring is provided with a mounting groove, the end face provided with the plurality of power grooves is arranged close to one end face of the graphite ring, the sealing ring and the graphite ring are mounted in the mounting groove of the retaining ring, the sealing ring, the graphite ring and the retaining ring are coaxially arranged, a gap is arranged between the other end face of the graphite ring and the mounting groove, and the distance of the gap is L.)

1. The utility model provides a gas turbine is mechanical non-contact end face seal system for bearing chamber which characterized in that: the sealing ring comprises a sealing ring (1), a graphite ring (2) and a retaining ring (3); sealing ring (1), graphite ring (2) and retaining ring (3) are the ring body, a terminal surface of sealing ring (1) has a plurality of power slots (1-1) along radially processing, processing has the mounting groove on retaining ring (3), the terminal surface that processing has a plurality of power slots on sealing ring (1) is close to a terminal surface setting of graphite ring (2), install in the mounting groove of retaining ring (3) sealing ring (1) and graphite ring (2), sealing ring (1), graphite ring (2) and retaining ring (3) coaxial setting, be equipped with the clearance between another terminal surface of graphite ring (2) and the mounting groove, the distance in clearance is L.

2. The mechanical non-contact end face sealing system for a gas turbine bearing cavity according to claim 1, wherein: the plurality of power grooves (1-1) are uniformly distributed on the end surface of the sealing ring (1) along the radial direction.

3. The mechanical non-contact end face sealing system for a gas turbine bearing cavity according to claim 1 or 2, wherein: the length direction of each dynamic groove (1-1) is arranged along the radial direction of the sealing ring (1).

4. The mechanical non-contact end face sealing system for a gas turbine bearing cavity according to claim 1 or 2, wherein: the distance between one end of each power groove (1-1) close to the circle center is smaller than the distance between the inner side wall of the graphite ring (2) and the circle center, and the distance between one end of each power groove (1-1) far away from the circle center is smaller than the distance between the outer side wall of the graphite ring (2) and the circle center.

5. The mechanical non-contact end face sealing system for a gas turbine bearing cavity according to claim 1, wherein: the outer side wall of the sealing ring (1) is provided with an annular bulge, the diameter of the outer side wall of the sealing ring (1) is smaller than that of the outer side wall of the graphite ring (2), and the diameter of the outer side wall of the graphite ring (2) is smaller than that of the mounting groove in the retaining ring (3).

Technical Field

The invention relates to a sealing system, in particular to a mechanical non-contact end face sealing system for a bearing cavity of a gas turbine.

Background

Disclosure of Invention

The invention provides a mechanical non-contact end face sealing system for a gas turbine bearing cavity, aiming at solving the problems that the sealing system is easy to fail due to the fact that the existing gas turbine bearing cavity is sealed by a spring rubber ring, lubricating oil and oil gas thereof are sucked into a main flow path in a large quantity, the working characteristics of blades are influenced, the combustion condition of a combustion chamber is deteriorated, and carbon deposition is generated.

The technical scheme adopted by the invention for solving the problems is as follows:

the sealing ring comprises a sealing ring, a graphite ring and a retaining ring; the sealing ring, the graphite ring and the retaining ring are annular bodies, a plurality of power grooves are formed in one end face of the sealing ring along the radial direction, a mounting groove is formed in the retaining ring, the end face, with the plurality of power grooves, of the sealing ring is arranged close to one end face of the graphite ring, the sealing ring and the graphite ring are mounted in the mounting groove of the retaining ring, the sealing ring, the graphite ring and the retaining ring are coaxially arranged, a gap is formed between the other end face of the graphite ring and the mounting groove, and the distance between the gap and the mounting groove is L.

The invention has the beneficial effects that:

1. the sealing system adopts non-contact end face sealing, prolongs the service life of a bearing cavity of the gas turbine, can adapt to variable working condition characteristics, has low leakage rate, high efficiency and compact structure, and is adopted by a compressor part of a high-power gas turbine.

2. Compared with a common spring rubber ring sealing system, the sealing system can meet the requirement of large-scale pressure difference change fluctuation between the bearing cavity and the sealing gas, and meanwhile, due to the good lubricating and heat dissipation characteristics of graphite, the working life of the sealing system can be greatly prolonged. Compared with a common spring rubber ring sealing system, the invention has the following advantages: when the gas turbine operates under a low working condition, the rotating speed of the rotor system is low, the working surface of the sealing ring is in contact with the graphite ring, the sealing system almost has no leakage at the moment, and due to the special self-lubricating property of graphite, the graphite ring almost has no abrasion when in contact operation, so that the reliable operation of the system at the rotating speed can be ensured; when the gas turbine runs under high working conditions, the rotating speed of a rotor system is high, at the moment, gas flowing into a power groove at the end face of a sealing ring is compressed to generate local high pressure due to the hydrodynamic pressure effect, a graphite ring in contact with the gas is pushed away, gas pressure balance is formed between oil gas of a bearing cavity and sealing gas, a working gap matched with the graphite ring is formed, pressure generated between the sealing ring and the graphite ring is blocked, gas flowing between the bearing cavity and the sealing gas is blocked, the minimum leakage amount is generated, and at the same time, the sealing system is almost in an infinite service life state due to the fact that the graphite ring and a moving ring are in a non-contact state at the moment.

Drawings

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

FIG. 2 is an enlarged sectional view taken along line M-M in FIG. 1.

Detailed Description