CN201611298U

CN201611298U - Axial-thrust balancing device

Info

Publication number: CN201611298U
Application number: CN2010201342060U
Authority: CN
Inventors: 谭旭刚; 卢伟; 石林; 王宇星
Original assignee: China Aircraft Power Machinery Institute
Current assignee: China Aircraft Power Machinery Institute
Priority date: 2010-03-18
Filing date: 2010-03-18
Publication date: 2010-10-20
Anticipated expiration: 2020-03-18

Abstract

The utility model relates to an axial-thrust balancing device, comprising an inner ring, an outer ring and a compressor rotor, wherein a double-layer labyrinth ring is arranged between the compressor rotor and the inner ring and fixedly connected with the compressor rotor and a vent hole communicated with a lower pressure cavity is opened on the inner ring to be connected with an atmosphere hole. The axial-thrust balancing device has features of small number of the parts, simple structure, easy realization, no need for external air source, good economical efficiency, assemble realization without need for decomposing the rotor after dynamic balance of rotor, high dynamic balance of the rotor, reduced rotor span and being favorable for pushing the rotation speed on the test piece.

Description

A kind of axial thrust balancing devices

Technical field

The utility model relates to a kind of balance device, relates to a kind of aeromotor test pneumatic plant axial thrust balancing devices particularly.

Background technology

The fundamental purpose of aero-engine compressor test is in order to verify the aeroperformance of engine compressor.When pneumatic plant was worked, the axial load that acts on the ball bearing often surpassed the rated load that bearing can bear, and for guaranteeing the bearing nonoverload, generally is once to establish balancing frame in the rotor rear end, realizes by draw gases at high pressure before balancing frame.Such structure has increased the fulcrum span, influences the raising of dynamic balance accuracy and rotating speed.And need external air source and the special-purpose gas circuit of obturaging, make complex structure.

Summary of the invention

The purpose of this utility model is: be slightly larger than in the testpieces axial force under the situation of loading ability of bearing, provide a kind of simple in structure, easy to manufacture, easily the assembling and the high axial thrust balancing devices of dynamic balance accuracy.

Axial thrust balancing devices of the present utility model includes outer shroud, interior ring and compressor rotor, it is characterized in that having additional the comb ring gear between described compressor rotor and the interior ring, and this comb ring gear and compressor rotor are solidly connected; Have the air hole that communicates with low-pressure cavity in described on the ring and communicate with gross blow hole.

In order better to realize above-mentioned purpose, described comb ring gear is double-deck comb ring gear.

Axial force device of the present utility model with the advantage that existing balancing disc type structure is compared is: the part number is few, and is simple in structure, is easy to realize, do not need external air source, good economy performance; Do not need to decompose rotor behind the rotor dynamic balancing and promptly can realize assembling, rotor dynamic balancing precision height; The rotor span reduces, and helps push-jump speed on the testpieces.

Description of drawings

Fig. 1 is the utility model structural representation.

Among the figure 1, compressor rotor, 2., the comb ring gear, 3, interior ring, 4, low-pressure cavity, 5, high pressure chest, 6, grate flow channel, 7, air hole, 8, outer shroud, 9 gross blow holes.

Embodiment

As shown in Figure 1, include outer shroud 8, interior ring 3 and compressor rotor 1, have additional comb ring gear 2 between compressor rotor 1 and the interior ring 3, this comb ring gear 2 is for bilayer and work the effect of obturaging, comb ring gear 2 usefulness nuts are connected on the compressor rotor 1, and the twice comb tooth on it contacts with two anchor rings of interior ring 3.Comb ring gear 2 has been divided into high pressure chest 5 and low-pressure cavity 4 with the space between compressor rotor 1 and the outer shroud 8, has the air hole 7 that communicates with low-pressure cavity 4 on the interior ring 3 and joins with gross blow hole 9.High pressure chest 5 communicates with grate flow channel 6.During work, part high pressure draught in the grate flow channel 6 enters high pressure chest 5, high pressure chest 5 stream pressures are greater than the pressure of low-pressure cavity 4, because the comb tooth effect on the comb ring gear 2, high pressure draught in the high pressure chest 5 can not flow to low-pressure cavity 4, and this just produces pressure differential on comb ring gear 2, and this pressure differential generation responsive to axial force backward is on comb ring gear 2, and pass to compressor rotor 1 to offset axial force forward, reach rotor dynamic balancing.

Claims

1. axial thrust balancing devices, include outer shroud (8), interior ring (3) and compressor rotor (1), it is characterized in that: have additional comb ring gear (2) between described compressor rotor (1) and the interior ring (3), this comb ring gear (2) is solidly connected with compressor rotor (1); Ring has the air hole (7) that communicates with low-pressure cavity (4) on (3) and joins with gross blow hole (9) in described.

2. according to the described axial thrust balancing devices of claim 1, it is characterized in that: described comb ring gear (2) is double-deck comb ring gear.