CN201103419Y

CN201103419Y - Second last blade of macrotype supercritical air cooling turbine

Info

Publication number: CN201103419Y
Application number: CNU2007201175672U
Authority: CN
Inventors: 王丽华; 李宇峰; 丁怀臣; 张春梅; 梅永林; 李庆
Original assignee: Harbin Turbine Co Ltd
Current assignee: Harbin Turbine Co Ltd
Priority date: 2007-12-03
Filing date: 2007-12-03
Publication date: 2008-08-20
Anticipated expiration: 2017-12-03

Abstract

The utility model discloses a secondary last stage blade of a supercritical air-cooling turbine, relating to the blade of the turbine, which aims at solving the problem that the current secondary last stage blade with unstable quality, low efficiency and short service life has serious impact on safe operation of the turbine. A working part (1) of the blade is 530mm in length (Ld) and a root of the working part (1) of the blade is 167.5mm in axial width (B); a cover band (2) is 39.15mm in width (B1); an intermediate (3) is 23.2mm in height (Hz); a blade root (4) is an oblique tooth and fir tree type and is 182mm in axial width (W) and 83.9856mm in total height (K). The design of the secondary last stage blade of the air-cooling turbine combines safety and high efficiency to guarantee the safe and efficient operations of the air-cooling turbine units in variable conditions.

Description

A kind of large and super-critical air cooling turbine second last stage blade

Technical field

The utility model relates to a kind of turbine blade.

Background technique

Air-cooled Unit is a kind of typical variable parameter operation unit, with respect to clammy unit, the design back pressure height and the back pressure excursion of Air-cooled Unit are big, the variation of ambient temperature scope of atmosphere is big, and second last stage blade is in transition zone usually, environment is more abominable, and is also more strict to its pneumatic and requirement of strength.Existing second last stage blade quality instability, efficient is low, and working life is short, has had a strong impact on the safe operation of steam turbine.

The model utility content

The purpose of this utility model is for solving existing second last stage blade quality instability, and efficient is low, and working life is short, has had a strong impact on the problem of the safe operation of steam turbine, and a kind of large and super-critical air cooling turbine second last stage blade is provided.The utility model is made up of blade working part 1, shroud 2, intermediate part 3 and blade root 4, shroud 2, blade working part 1, intermediate part 3 and blade root 4 are connected as a single entity from top to bottom, the molded lines of blade working part 1 is the variable cross section twisted blade, along blade height sectional shape difference, sectional area is reduced toward the top gradually by root, has relatively between adjacent two sections and reverses; The geometric data in variable cross section twisted blade cross section: the depth of section in A-A to N-N cross section number is 0～530mm; Axial width is 167.5～39.153mm; Chord length is 185.023～152.307mm; Inlet angles are 53.7352 °～161.7759 °; Established angle is 65.0342 °～14.5455 °; Maximum ga(u)ge is 29.365～5.640mm; Trailing edge thickness is 1.518～1.537mm; Blade root 4 is helical teeth fir-tree roots.

The utlity model has following beneficial effect: the utility model is that the Security and the high efficiency of Air-cooled Unit second last stage blade design organically combines, and guarantees Air-cooled Unit variable working condition safe and highly efficient operation.The utlity model has following advantage: 1. with one dimension/standard three-dimensional/complete three-dimensional pneumatic, thermodynamic analysis calculates this second last stage blade and adopted the full three dimensional design of bending united forming, movable vane forms the compound bending chip level that comes into leaves along counter the turning round of leaf height.2. vane tip adopts and carries shroud, reduces the loss, and the multi-disc gland sealing gear can be assembled in the top, and anti-leak-stopping vapour improves unit efficiency.3. blade root is adopted the helical teeth fir-tree root, and it has the bearing capacity height, and is easy for installation, and the little advantage of impeller axial width, adopts the helical teeth fir-tree root can guarantee that whole circle is packed into together when assembling.

Description of drawings

Fig. 1 is a plan view of the present utility model, and Fig. 2 is a side view of the present utility model, and Fig. 3 is a plan structure schematic representation of the present utility model, and Fig. 4 is the superimposed schematic representation of vane type line of the present utility model.

Embodiment

Embodiment one: (referring to Fig. 1～Fig. 4) present embodiment is made up of blade working part 1, shroud 2, intermediate part 3 and blade root 4, shroud 2, blade working part 1, intermediate part 3 and blade root 4 are connected as a single entity from top to bottom, the height Ld of blade working part 1 is 530mm, the root axial width B of blade working part 1 is 167.5mm, the molded lines of blade working part 1 is the variable cross section twisted blade, along blade height sectional shape difference, section area is gradually little, has relatively between adjacent two sections and reverses; The width B 1 of shroud 2 is 39.15mm; The height H z of intermediate part 3 is 23.2mm; Blade root 4 is helical teeth fir-tree roots, can guarantee the best stress of rotor like this, and avoid peak stress occurring in each tooth root portion and supporting plane that axial width W is 182mm, and total height K is 83.9856mm, and it can guarantee that whole circle is packed into together when assembling.

The geometric data in variable cross section twisted blade cross section: the depth of section in A-A to L-L cross section number is 0～530mm; Axial width is 167.5～39.153mm; Chord length is 185.023～152.307mm; Inlet angles are 53.7352 °～161.7759 °; Established angle is 65.0342 °～14.5455 °; Maximum ga(u)ge is 29.365～5.640mm; Trailing edge thickness is 1.518～1.537mm;

Table 1: each cross section basic parameter:

Claims

1, a kind of large and super-critical air cooling turbine second last stage blade, it is made up of blade working part (1), shroud (2), intermediate part (3) and blade root (4), shroud (2), blade working part (1), intermediate part (3) and blade root (4) are connected as a single entity from top to bottom, the molded lines of blade working part (1) is the variable cross section twisted blade, along blade height sectional shape difference, section area is gradually little, has relatively between adjacent two sections and reverses; The geometric data that it is characterized in that variable cross section twisted blade cross section: the depth of section in A-A to L-L cross section number is 0～530mm; Axial width is 167.5～39.153mm; Chord length is 185.023～152.307mm; Inlet angles are 53.7352 °～161.7759 °; Established angle is 65.0342 °～14.5455 °; Maximum ga(u)ge is 29.365～5.640mm; Trailing edge thickness is 1.518～1.537mm.

2, a kind of large and super-critical air cooling turbine second last stage blade according to claim 1, the width (B1) that it is characterized in that shroud (2) is 39.15mm.

3, a kind of large and super-critical air cooling turbine second last stage blade according to claim 1 is characterized in that the height (Hz) of intermediate part (3) is 23.2mm.

4, a kind of large and super-critical air cooling turbine second last stage blade according to claim 1 is characterized in that blade root (4) is the helical teeth fir-tree root, and axial width (W) is 182mm, and total height (K) is 83.9856mm.