CA2562712C

CA2562712C - Steam/gas turbine pressure stage with universal shroud

Info

Publication number: CA2562712C
Application number: CA2562712A
Authority: CA
Inventors: Vladlen Zitin; Oleg Naljotov
Original assignee: Individual
Current assignee: Individual
Priority date: 2003-04-18
Filing date: 2003-04-18
Publication date: 2011-05-31
Anticipated expiration: 2023-04-18
Also published as: CN1788142A; EP1623097A4; BR0318261A; EP1623097A1; AU2003228590A1; EA200501572A1; JP4195882B2; UA81314C2; JP2006523792A; WO2004099572A1; HK1092853A1; EA008156B1; AU2003228590B2; CA2562712A1; CN100386502C

Abstract

There is provided a steam turbine pressure stage designed with a nozzle (directional) block with nozzle (directional) blades and shield, a rotor wheel, consisting of disc, rotor blades, a shroud and shroud seals, incorporated in the nozzle block or located on the shroud of rotor blades.

Description

TITLE
[0001] Steam/gas turbine pressure stage with universal shroud FIELD

[0002] This relates to the manufacture and operation of steam and gas turbines, compressed air plants and gas force pumps.

[0003] Imperfect design of belt shrouds or identical parts of the blades of such machines, including the adjoining seals, leads to the decrease in reliability and efficiency.
1. Uneven distribution of radial clearances along the shrouds' circumference induces the effect of air-dynamic Thomas forces, decreasing vibration behavior.
2. The inner surface of shrouds is subjected to formation of metal oxide and salt deposits.

[0004] These drawbacks are eliminated by way of drilling of radial holes in the shrouds of the blades. The transfer of steam through the shroud holes results in the relief of the pressures gradient on the surface of the shroud and prevents the formation of metal oxide, salt and other deposits on the inner surfaces of the shrouds.

[0005] The quantity and diameter of the holes, as well as their corresponding disposition and the values of radial clearances in shroud crowning seals regulate their efficiency.
BACKGROUND

[0006] Steam or gas turbine stages possess the following significant flaws, revealed in the course of turbine operation:
a) Due to the uneven distribution of clearances in shroud seals around the stage, there emerge air dynamic shroud and ridge Thomas forces, inducing unstable operation of turbine rotor and its supports;
b) Inner surface 8 of rotor blade shroud is subject to the formation of metal and salt oxides 10, the presence of which closes a portion of rotor blade open flow area, which leads to the decrease of rated efficiency factor with subsequent reduction of turbine power.
c) Excessive fuel combustion, owing to p. b) with varying comparative turbine loads leads to the extra consumption of fuel resources.
SUMMARY

[0007] The purpose of the steam/gas turbine pressure stage with universal shroud is the improvement of steam and gas turbines operation reliability, the increase of actual efficiency factor and power as compared to the existing parameters.

[0008] There is provided a steam turbine pressure stage designed with a nozzle (directional) block with nozzle (directional) blades and shield, a rotor wheel, consisting of disc, rotor blades, a shroud and shroud seals, incorporated in the of the nozzle block or located on the shroud of rotor blades.

[0009] Shroud seals of a turbine stage consist as a rule of two ridges, with the first ridge following the direction of steam flow located in the seal and the second ridge, both of which form a shroud chamber, located over the shroud, comprising radial clearances hl and h2, determining the flow rate of steam, coming through seal.

[0010] Clearances hl and h2 are set equal in absolute value for each stage or stage group, the value depending on the conditions of thermal expansion of turbine parts, as well as on the conditions of turbo-unit threshold power, i.e. power, producing low frequency vibration.
Rotor blade shroud, are in the form of a strip with openings for rotor blade pins, which are unriveted after their mounting on rotor blades, forming a pack of six or more blades. Parts of the shroud, covering single flow channel do not have any openings. The ratio between the number of openings n and their diameter d is the following:

d-2 0.02-20.50). Sk nor where Sk is the surface area of the outer shroud, covering each single inter-blade channel in rotor wheel.

BRIEF DESCRIPTION OF THE DRAWINGS

[0011] These and other features will become more apparent from the following description in which reference is made to the appended drawings, the drawings are for the purpose of illustration only and are not intended to be in any way limiting, wherein:
FIG. 1 is a longitudinal section of turbine pressure stage with shroud seals in the nozzle block shield.
FIG. 2 is a longitudinal section of turbine pressure stage with shroud seals, located in rotor blade shrouds FIG. 3 is a shroud section of FIG. 1.
FIG. 4 is a shroud section of FIG. 2.
FIG. 5 is a detail of FIG. 4 with section along D-D
FIG. 6 is a detail of FIG. 3 with section along C-C
DETAILED DESCRIPTION

[0012] A steam (gas) turbine (compressor) pressure stage FIG. 1 and FIG.2.
comprising a nozzle (directional) block 1 with nozzle (directional) blades 2 and a shield 3, seal shroud ridges 4 and 5 or ridges 4 and 5, located on the shroud 8 FIG.2 and rotor wheel with shroud 8, located on rotor blades 7 differs in the respect, that with the purpose of increasing the efficiency factor and operational reliability of turbine, radial clearance h2 of the second ridge 5 of shroud seal, located along the steam/gas flow is made less than radial clearance hl of the ridge 4 of the shroud seal and in parts 13, 14, 15 of the shroud 8, closing the single inter-blade channel there is a system of radial discharge openings 12 FIG.3, FIG.4, FIG.5 and FIG.6, distributed evenly in relation to the surfaces of parts 13, 14, 16 of shroud 8. The radial discharge openings can also be organized in staggered order 16, as well as along medium steam flow line 14 and 18, or in symmetrical position to steam flow line 18 FIG.4 in the inter-blade channel, for steam (gas) overflow from the enclosure 17 above the shroud FIG.5 and chamber 11 above the shroud to the flow channel and the discharge of above shroud pressure, the pressure being the source of air dynamic above shroud and ridge "Thomas forces", which induce unstable operation of turbine rotor and its supports, whereas steam (gas), entering through the discharge openings 12 in shroud 8 to the above shroud enclosure of the flow channel prevents the formation of metal and salt oxides 10 on the inner surface of shroud 8 with the diameter d of the openings 12 and their number n on each surface Sk of each flow channel of shroud parts 13, 14, 16, covering the single inter-blade channel stand in the following ratio:

d=2 0.02=0.50 - Sk n-z [0013] Improvement of steam and gas turbines operation reliability, the increase of actual efficiency factor and power is achieved by way of making of clearances hl and h2 in the ridges of shroud seals in such a manner, that the radial seal h2 on the second ridge 5 is smaller than the radial clearance hl on the first ridge 4, which permits to regulate the flow rate of steam, coming through shroud chamber 11 within specified limits. A system of discharge openings 12 is implemented in rotor blade shroud parts 13, covering single inter-blade channel, by way of drilling of the shroud FIG. 5 and FIG.6. The openings are located evenly along the surface of parts 13 and 14 of the shroud 8, following the direction of steam flow 18 FIG. 4 in inter-blade channel 14. The openings may be organized in staggered order 16, depending on the properties of deposits and their volume, as well as on seals design.

[0014] Due to openings 12 in the shroud 8 of rotor blades 7 there occurs in the course of turbine operation a steam overflow from the chamber 11 located above the shroud and enclosure 17, also above the shroud FIG. 5 to the part of flow channel, located under the shroud, which leads to the creation of an obstacle effect, preventing the formation of metal and salt oxides on the inner surface of the shroud.

[0015] The discharge of pressure from the chamber 11 located over the shroud and enclosure 17 over the shrouds is implemented by similar process of steam overflow, which process excludes the onset of air dynamic above shroud and ridge Thomas forces, inducing unstable operation of turbine rotor and its supports. This, in turn, facilitates the reduction of radial clearance h2 on the second ridge 5, controlling the turbo-unit threshold power, which results in additional increase of the efficiency factor owing to the reduction of steam overflow over the seal.

[0016] Thus, the steam/gas turbine can be used for the following purposes:
a) as means, preventing the formation of metal and salt oxides on the inner surfaces of rotor blade shrouds;
5 b) as means for the enhancement of turbo-unit vibration state c) with the purpose of prolongation of period between repairs owing to p.p. a) and b) and that of turbine service life.

[0017] In this patent document, the word "comprising" is used in its non-limiting sense to mean that items following the word are included, but items not specifically mentioned are not excluded. A reference to an element by the indefinite article "a" does not exclude the possibility that more than one of the element is present, unless the context clearly requires that there be one and only one of the elements.

[0018] The following claims are to be understood to include what is specifically illustrated and described above, what is conceptually equivalent, and what can be obviously substituted. Those skilled in the art will appreciate that various adaptations and modifications of the described embodiments can be configured without departing from the scope of the claims. The illustrated embodiments have been set forth only as examples and should not be taken as limiting the invention. It is to be understood that, within the scope of the following claims, the invention may be practiced other than as specifically illustrated and described.

Claims

What is claimed is:

1. An axial flow fluid machine for use with steam or gas comprising:
a stationary housing;
a rotor member having an inner disc, an outer shroud, and a plurality of blades mounted between the disc and the shroud;
shroud seals including two sealing combs located either on an outer surface of the outer shroud or on an inner surface of the stationary housing radially facing the outer shroud, the two sealing combs providing two radial clearances h1 and h2 between the rotor member and the housing, the clearance h2 being less than the clearance h1; and a plurality of radial discharge openings arranged in the outer shroud, the openings being distributed either evenly or staggered such that steam or gas flowing radially outwardly through the openings prevents the formation of metal and salt oxides on the inner surface of the outer shroud and wherein the diameter d of the openings, the number n of the openings, and the surface area Sk of the outer shroud covering the flow channel through the rotor satisfies the relationship: