CN202510170U - Device for cooling gas turbine blade - Google Patents

Abstract

The utility model relates to a device for cooling a gas turbine blade. Fused salt is utilized as a cooling medium, a new blade inside-channel is designed for cooling, and an air film is not utilized for cooling. The leading edge of the blade is cooled by utilizing a jet impact hole and a turbulence strengthening device in a cooling channel, and other parts of the blade are cooled by utilizing the blade inside-channel. After the fused salt enters a blade cavity body, the fused salt flows through the blade cavity body along the cooling channel to cool the pressure surface and the suction surface of the blade and the trailing edge of the blade for one time, part of the fused salt forms jet impact cooling at the leading edge of the blade, then the fused salt is discharged from an outlet of the cooling channel at the root of the blade to form a closed U-shaped cooling loop, and the integral cooling to the blade is completed. The temperature of the turbine blade can be kept within 600 DEG C through the cooling device, the compressed air is not consumed, and a lot of inner structures of the blade are simplified. The processing technology and the material requirement of the blade are reduced, the strength of the blade is enhanced, and the service life of the blade is prolonged. The manufacture cost of a gas turbine is significantly reduced, and the shaft work power of the gas turbine is increased.

Description

The device of cooling gas turbine blade

Technical field

The utility model relates to the cooling structure of gas turbine blades.

Background technique

Gas turbine is the core component in resource equipment field, and military affairs and industrial field all have important function on aviation, naval vessel, land etc.Along with improving constantly of advanced gas turbine turbine inlet fuel gas temperature; Manufacturing process to the turbine high-temperature component requires to have proposed more harsh challenge with cooling; Present advanced gas turbine turbine inlet fuel gas temperature has surpassed 1500 ℃; And further march toward 1900 ℃ and even higher temperature, and the operating temperature of present senior nickel-base alloy is below 1100 ℃, in order to guarantee the life-span of high-temperature turbine blade; Need adopt strong cooling way to it, so that the temperature field of blade integral and stress distribution all remain on reasonable level.

At present state-of-the-art in the world turbine rotor blade all adopts very complicated many inner-cavity structures, combines air film cooling, jet impulse cooling, the multiloop turbulent flow of air to promote forced-convection heat transfer, trailing edge pin rib flow-disturbing cools off and technology such as advanced PVD heat insulating coat guarantee that blade works in the design temperature scope.Further raising along with turbine fuel gas inlet temperature; The lifting effect of this dependence pressurized air cooling turbine bucket is more and more fainter; On the one hand because the increase of heat; The air quantity that is used for cooling turbine bucket up to the total tolerance of pressurized air 20% or higher, caused the consumption of a large amount of power, had a strong impact on the performance of gas turbine; On the other hand, when improving the air compression ratio, inevitably also can improve the temperature of cooling air, reduce the thermal capacitance of cooled gas, increase the cooling difficulty.

In order to realize the further fast development of advanced gas turbine, press for a kind of technique for cooling blades of gas turbine revolutionary, Ultra-High Efficiency that has.

The model utility content

The purpose of the utility model provides a kind of turbine blade of gas turbine cooling means; This cooling means can be controlled at Turbine Blade Temperature Field in 600 degrees centigrade; And consumption of compressed air is not simplified the blade interior structure simultaneously, reduces blade processing technique and requires and cost; Strengthen blade strength and working life, significantly improve gas turbine proficiency.

The utility model adopts following technological scheme for realizing above-mentioned target:

The utility model provides the device of cooling gas turbine blade.Utilize fuse salt to be cooling working medium, designed brand-new blade internal channel cooling, no longer utilize the cooling of fish scale hole and air film.Cooling is realized with the turbulent flow intensifier 10 in the cooling channel in jet impulse hole 4, and other positions of blade utilize blade U-shaped internal channel to cool off.After fuse salt gets into the blade cavity; 6,7,11, the 12 blade cavitys of flowing through along the cooling channel; Cooled blade pressure side 15 and suction surface 18 and blade trailing edge 19, partial melting salt forms the jet impulse cooling at blade inlet edge 16, discharges from fuse salt inlet then; Form conventional closed cooling loop, accomplish integral body cooling blade.

The device of cooling gas turbine blade; Turbine blade includes the bucket platform 2 of vane foil 3, blade root 1 and blade root; The vane foil outer surface is made up of pressure side 15 and suction surface 18, and what connect pressure side 15 and suction surface 18 is respectively blade inlet edge 16 and blade trailing edge 19; It is characterized in that: said turbine blade cooling working medium is a fuse salt;

Vane foil inside is divided into blade inlet edge cooled region and blade trailing edge cooled region by the cooling channel demarcation strip; The blade inlet edge cooled region is separated into 3 cooling channels by the cooling channel demarcation strip of U-shaped; It is respectively the first impact cooling channel 6; Be furnished with jet impulse hole 4 on the cooling channel demarcation strip of the second impact cooling channel 7 and be shaped cooling internal channel 12, the first cooling impact passages 6 and the second impact cooling channel 7;

Inlet 14 gets into the second impact cooling channel 7 to fuse salt from the root of blade cooling channel; Get into the first impact cooling channel 6 through the jet impulse hole on the demarcation strip of cooling channel 4; Flow into the cooling internal channel 12 that is shaped then, flow out by root of blade cooling channel outlet 13 at last;

The blade trailing edge cooled region is separated by the cooling channel demarcation strip and forms the blade trailing edge cooling channel 11 and the cooling internal channel 12 that is shaped, and both communicate and form the cooling circuit of a U-shaped;

Inlet 14 gets into blade trailing edge cooling channel 11 to fuse salt from the root of blade cooling channel, and the shaping cooling channel 12 of flowing through is then flowed out by root of blade cooling channel outlet 13 at last, accomplishes the cooling to whole blade.

Described cooling working medium is liquid fused salt of various single pure substances or mixed melting salt, and described cooling working medium is various organic and inorganic salts, metallic oxide and their mixture.

Further, be furnished with turbulent flow intensifier 10 in the cooling channel.

The method of described fuse salt cooling gas turbine blade, because fuse salt refrigerant heat transfer superior performance, the blade cooling is all accomplished by the blade interior cooling channel, no longer need design the air film cooling structure.

The method of described fuse salt cooling gas turbine blade, the fuse salt blade U-shaped inner cooling path of once flowing through can be accomplished the cooling to blade.

The method of described fuse salt cooling gas turbine blade, the blade inner-cooling structure has carried out a large amount of simplification, no longer need design fish scale hole and blade trailing edge exhaust port that leading edge is used for the air film cooling.

The method of described fuse salt cooling gas turbine blade; The jet impulse that utilizes fuse salt is to blade inlet edge 16 coolings; The cooling of blade pressure surface 15, suction surface 18 and trailing edge 19 is directly accomplished by flow through inner cooling path 6,7,11,12 of fuse salt, is furnished with turbulent flow intensifier 10 in the cooling channel.

The utlity model has following advantage and high-lighting effect: the employed fuse salt cooling working medium of the method temperature conductivity of the utility model fuse salt cooling gas turbine blade is the hundred times of high temperature compressed air working medium, can rapidly leaf temperature be reduced in the design temperature scope; Be the liquid single-phase forced-convection heat transfer cooling that utilizes fused salt, need do not utilize latent heat of phase change; The cooling effect highly significant can (fuse salt jet impulse heat exchange equation be: Nu=1.29Re at 500～600 degrees centigrade with the blade wall temperature control ^0.5Pr ^1/3, the interior forced-convection heat transfer of pipe fully develops turbulent equation and is: Nu=0.024Re ^0.87Pr ^0.331, forced-convection heat transfer transition flow heat exchange equation is in the pipe: $\mathrm{Nu}=0.007({\mathrm{Re}}^{0.92}-280){\mathrm{Pr}}^{0.4}[1+{\left(\frac{d}{l}\right)}^{2/3}]{\left(\frac{{\mathrm{Pr}}_f}{{\mathrm{Pr}}_w}\right)}^{0.11}$ Wherein d is a round tube inside diameter, and l is a pipe range); Do not re-use pressurized air as cooling working medium, avoided fully because cooled blade and splitter section pressurized air to the power consumpiton of gas turbine, have significantly increased gas turbine shaft work power; The design and the manufacture difficulty of blade have significantly been reduced; After using fuse salt as heat-transfer working medium; The turbine blade internal cooling channel can be simplified in a large number; The blade inner-cooling structure has carried out a large amount of simplification, no longer need design fish scale hole and blade trailing edge exhaust port that leading edge is used for the air film cooling, only needs the fuse salt cooling channel flow process of simplicity of design to get final product; Blade material no longer is confined to senior nickel-base alloy, because the reduction of blade working temperature and structural requirement, blade material can adopt low side alloy even common stainless steel; Limited by harsh cooling processing conditions, improved blade life-span, reduced the blade manufacture cost.These advantages can fundamentally interrupt external technical monopoly to hot-end component.

Description of drawings

Fig. 1, the blade 3-D view.

Fig. 2, the internal structure schematic representation that the utility model is cut blade open along the blade mean camber line.

Fig. 3 is the plan view that Fig. 1 removes top closure.

Wherein, in Fig. 1～3: the 1-blade and blade is followed; The 2-bucket platform; The 3-vane foil; 4-jet impulse hole; 5-impacts the cooling demarcation strip; The 6-first impact cooling channel; The 7-second impact cooling channel; 8-cooling channel demarcation strip; The 9-top closure; 10-turbulent flow intensifier; 11-blade trailing edge cooling channel; 12-is shaped and cools off internal channel; The outlet of 13-root of blade cooling channel; 14-root of blade cooling channel inlet; The 15-pressure side; The 16-blade inlet edge; 17-blade mean camber line; The 18-suction surface; The 19-blade trailing edge.

Embodiment

Below in conjunction with accompanying drawing principle, practical implementation and the working procedure of the utility model are done further explanation.

Accompanying drawing has provided a specific embodiments of the utility model, and Fig. 1 is the 3-D view of gas turbine high temperature turbine blade, comprising vane foil 3, blade and blade with 1 and the bucket platform 2 that connects both.Along blade mean camber line 17 blade is cut open, it is as shown in Figure 2 to obtain the blade interior structure.Blade interior has and is used to cool off a plurality of cooling channels 6,7,11,12 that fuse salt flows; Fuse salt (the for example mixed melting salt of mass percent 40% potassium nitrate and 60% sodium nitrate composition) gets into blade inner cooling paths 6 and 11 by root of blade cooling channel inlet 14; The inner cooling path 7,12 of flowing through respectively, then still from the root of blade cooling channel outlet 13 flow out and form complete cooling circuit.

Shown in the scheme blade interior 6,7,11,12 and two cooling circuits in five cooling channels are arranged; Cooling circuit comprises that the fuse salt that is used for blade inlet edge 16 coolings impacts cooling circuit, is used for the reinforcement convection current cooling circuit of blade middle part and blade trailing edge 19 zone coolings.One fuse salt is used to carry out the impact cooling of blade inlet edge 16, forms and impacts cooling circuit; Other fuse salts then get into corresponding cooling channel and utilize the reinforcement convection heat exchange to realize the cooling to blade middle part and trailing edge.

In this case study on implementation; Described fuse salt impacts cooling circuit and comprises the first impact cooling channel 6 and the second impact cooling channel 7; Said two impact cooling channels separate by impacting cooling demarcation strip 5; Arranged on the said impact cooling demarcation strip that at least one jet impulse hole 4, the first impact cooling channel wall arranged to have at least one turbulent flow intensifier 10 of strengthening the convection current cooling effect.

In this case study on implementation; Direct convection current cooling channel is adopted at the blade middle part; Each cooling channel is separated by cooling channel dividing plate 8, and the wall of each cooling channel has been arranged at least one turbulent flow intensifier 10, to strengthen fuse salt convection current cooling effect in the passage; The corresponding root of blade in each cooling channel is furnished with the jet impulse hole 4 that is different from import at least, and the fuse salt fluid should guarantee the opening outflow from then on of enough pressure.

Because the fuse salt cooling effect is good, the pin rib structure is not arranged in 11 inside, blade trailing edge cooling channel, fuse salt directly flow through the trailing edge passage from the root of blade cooling channel outlet 13 discharge.

The utility model has been described a case study on implementation of above-mentioned fuse salt working medium cooling gas turbine blade; But the utility model is not limited to the blade structure details of foregoing description and the heat transfer type of fuse salt; But contain the content that claims limit, and the equivalent structure that draws the neutralization distortion thus.

Claims (2)

1. the device of cooling gas turbine blade; Turbine blade includes the bucket platform (2) of vane foil (3), blade root (1) and blade root; The vane foil outer surface is made up of pressure side (15) and suction surface (18), and what connect pressure side (15) and suction surface (18) is respectively blade inlet edge (16) and blade trailing edge (19); It is characterized in that:

Vane foil inside is divided into blade inlet edge cooled region and blade trailing edge cooled region by the cooling channel demarcation strip; The blade inlet edge cooled region is separated into 3 cooling channels by the cooling channel demarcation strip of U-shaped; It is respectively the first impact cooling channel (6); The second impact cooling channel (7) and the cooling internal channel (12) that is shaped are furnished with jet impulse hole (4) on the cooling channel demarcation strip of the first cooling impact passage (6) and the second impact cooling channel (7); The blade trailing edge cooled region is separated by the cooling channel demarcation strip and forms blade trailing edge cooling channel (11) and the cooling internal channel (12) that is shaped, and both communicate and form the cooling circuit of a U-shaped.

2. the device of cooling gas turbine blade as claimed in claim 1 is characterized in that: be furnished with turbulent flow intensifier (10) in the cooling channel.

Images