CN101658895A

CN101658895A - Local loading forming method of thick plate of TA19 titanium alloy engine case of aero-engine

Info

Publication number: CN101658895A
Application number: CN200910026276A
Authority: CN
Inventors: 王金吕; 杨海东; 徐大懋
Original assignee: Wuxi Turbine Blade Co Ltd
Current assignee: Wuxi Turbine Blade Co Ltd
Priority date: 2009-03-19
Filing date: 2009-03-19
Publication date: 2010-03-03
Anticipated expiration: 2029-03-19
Also published as: CN101658895B

Abstract

The invention relates to local loading forming method of a thick plate of a TA19 titanium alloy engine case of an aero-engine. In the method, present forging devices are used adequately without addingdevices, and a local loading forming process of the thick plate is adopted to produce titanium alloy engine case forge pieces of the aero-engine with a projection area 0.3m<2>-0.5m<2>, thereby savingthe device purchasing capital and reducing the production cost. The method comprises the following steps: machining the TA19 titanium alloy material into a thick plate structure firstly; then placingthe thick plate of the titanium alloy material into a mould cavity of a local forming forging piece mould, forging and striking for 4 to 5 times so that the thick plate is locally loaded, wherein 50%of expansion area of middle part of the thick plate forms to a size of a final forging piece; then primarily blanking the rest to form the local forming forging piece; then cutting the raw edges; placing the local forming forging piece to the mould cavity of the local forming forging piece mould, forging and striking for 4 to 5 times; and obtaining the final forging piece by bending the final forging mould and forming the rest 50% area.

Description

The thick plate of TA 19 titanium alloy engine case of aero-engine local loading forming method

(1) technical field

The present invention relates to aero-engine casing forging and forming technology field, concrete thick plate of TA 19 titanium alloy engine case of aero-engine local loading and shaping technology.

(2) background technology

Owing to be subjected to the restriction of domestic large-sized forging equipment, aero-engine large titanium alloy casing forging all is shaped by isothermal forging, its shortcoming is: it is had relatively high expectations to mould, its die cost is 5 times～10 times of common forging mold cost, and isothermal forging productivity ratio is lower, and every production time is 3 times～5 times of common forging.

(3) summary of the invention

At the problems referred to above, the invention provides thick plate of TA 19 titanium alloy engine case of aero-engine local loading and shaping technology, it makes full use of existing forging equipment, under the situation that does not increase equipment, by adopting the slab local loading to form technology, can production projected area 0.3m ²～0.5m ²Aero-engine titanium alloy casing forging, saved the equipment purchasing fund, reduced production cost.

Its technical scheme is such, it is characterized in that: it comprises following procedure of processing:

1, the TA19 titanium alloy material is processed into thick plate structure;

2, described titanium alloy material slab is put in the partial plastic forming forging mold former chamber, forged 4 times～5 times, make slab pass through local loading, the flattening area of middle part 50% is formed into final forging ' s block dimension;

3, with the preliminary base of remainder, being shaped obtains partial plastic forming forging, cutting forming burr then;

4, described partial plastic forming forging is put in the final forging mold former chamber, forged 4 times～5 times, crooked and remaining 50% the area of being shaped obtains final forging by the finish-forging mould.

Use thick plate of TA 19 titanium alloy engine case of aero-engine local loading and shaping technology of the present invention to come forging and molding large titanium alloy casing forging, compare with isothermal forging forming technology in the past, its beneficial effect is: it requires lower to mould, die cost is low, and can improve working (machining) efficiency greatly.

(4) description of drawings

Fig. 1 is the titanium alloy thick plate structural representation;

Fig. 2 is a partial plastic forming forging structural representation;

Fig. 3 is final shaping forging structural representation.

(5) specific embodiment

Specifically describe process below in conjunction with accompanying drawing: at first just the TA19 titanium alloy material is processed into thick plate structure, sees Fig. 1; Then described titanium alloy material slab is put in the partial plastic forming forging mold former chamber, forged 4 times～5 times, make slab be formed into final forging ' s block dimension by the flattening area of local loading middle part 50%; With the preliminary base of remainder, being shaped obtains the partial plastic forming forging, sees Fig. 2, again the cutting forming burr; Described partial plastic forming forging is put in the final forging mold former chamber, forged 4 times～5 times, crooked and remaining 50% the area of being shaped obtains final forging by the finish-forging mould, sees Fig. 3.

Claims

1, thick plate of TA 19 titanium alloy engine case of aero-engine local loading forming method is characterized in that: it comprises following procedure of processing:

(1), the TA19 titanium alloy material is processed into thick plate structure;

(2), described titanium alloy material slab is put in the partial plastic forming forging mold former chamber, forge 4 times～5 times, make slab pass through local loading, the flattening area of middle part 50% is formed into final forging ' s block dimension;

(3), with the preliminary base of remainder, being shaped obtains partial plastic forming forging, cutting forming burr then;

(4), described partial plastic forming forging is put in the final forging mold former chamber, forge 4 times～5 times, crooked and remaining 50% the area of being shaped obtains final forging by the finish-forging mould.