CN104832219A - Turbine blade device with internal cooling function and gas turbine applying same - Google Patents
Turbine blade device with internal cooling function and gas turbine applying same Download PDFInfo
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- CN104832219A CN104832219A CN201510204514.3A CN201510204514A CN104832219A CN 104832219 A CN104832219 A CN 104832219A CN 201510204514 A CN201510204514 A CN 201510204514A CN 104832219 A CN104832219 A CN 104832219A
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- turbine blade
- cooling
- set according
- blade set
- heat exchanger
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Abstract
The invention provides a turbine blade device with an internal cooling function. The turbine blade device comprises a turbine blade body, wherein a cooling channel is formed inside the turbine blade body; in the cooling channel, NH3 is taken as a cooling medium. In the turbine blade device, the NH3 cooling medium performs convective heat exchange with a wall surface and also absorbs heat on the wall surface to perform a chemical reaction, so that a large amount of absorption heat is taken away, and the cooling efficiency is increased greatly.
Description
Technical field
The present invention relates to gas turbine and fluid dynamics techniques field, particularly relate to and a kind ofly there is the turbine blade set of internal cooling function and apply its gas turbine.
Background technique
Gas turbine, as a kind of novel power device, plays very important function in the various fields of national economy and national defense construction.Based on improve gas turbine performance in the urgent need to, the turbine inlet temperature (TIT) as one of large critical component of gas turbine three constantly raises, and reaches about 2200K at present, far above material melting point temperature.In order to ensure turbine blade safe and reliable operation in high temperature environments, effective cooling must be carried out to it.The cooling of turbine blade mainly launches from blade exterior and inner two aspects.In recent years, turbine blade internal cooling mode obtains fast development, and main cooling technology comprises impact jet flow cooling, the cooling of fin turbulence columns, post-rib cooling, and combination cooling.
At present, along with the further raising of turbine temperature, reduce for the inner colded air quantity of turbine blade, and the lifting of cooling air temperature, cause existing turbine blade internal cooling skill upgrading space more and more less, be difficult to the progress obtaining step evolution again.As can be seen here, the efficient turbine blade internal cooling technology of novelty must be proposed, thus ensure gas turbine safe and highly efficient operation under worst hot case.
Summary of the invention
(1) technical problem that will solve
In view of above-mentioned technical problem, the invention provides and a kind ofly there is the turbine blade set of internal cooling function and apply its gas turbine, to ensure that gas turbine equally can safe and reliable Effec-tive Function under worst hot case.
(2) technological scheme
The invention provides a kind of turbine blade set with internal cooling function, this turbine blade set comprises: turbine blade body, and its inside has cooling channel, in this cooling channel, adopt NH
3as cooling working medium.
(3) beneficial effect
As can be seen from technique scheme, the turbine blade set that the present invention has internal cooling function and the gas turbine applying it have following beneficial effect:
(1) improve turbine blade internal cooling efficiency, conventional air cooling is only inner at turbine blade, utilizes Cryogenic air to carry out convection heat exchange to high-temperature wall surface, and NH
3not only and between wall there is convection heat exchange in cooling working medium, but also absorbs the heat of wall, and chemical reaction occurs, and takes away a large amount of absorption heat;
(2) due to the raising of turbine blade internal cooling efficiency, allow higher Turbine Inlet Gas Temperature, nature can improve the thermal efficiency; From turbine blade high-temperature gas mixture out at synthesis NH
3process in also to the Cryogenic air heat release in gas compressor, contribute to improve the thermal efficiency; NH
3the existence of cooling air decreases the Cryogenic air from gas compressor for cooled blade, makes more air for work by combustion, contributes to improving the thermal efficiency;
(3) ammonia cost of material is lower, makes method economically feasible of the present invention;
(4) due to whole process sealing, recycling of ammonia, pollution-free, without dangerous, environment compatibility is good.
Accompanying drawing explanation
Fig. 1 is the structural representation of the turbine blade set according to the embodiment of the present invention with internal cooling function.
Embodiment
The present invention is with the NH of gaseous state
3for cooling working medium cools from inside turbine blade, cooling effectiveness is higher, ensures gas turbine safe and reliable operation, also has the advantage that cost is low, environment compatibility is good simultaneously.
For making the object, technical solutions and advantages of the present invention clearly understand, below in conjunction with specific embodiment, and with reference to accompanying drawing, the present invention is described in more detail.
In one embodiment of the invention, a kind of turbine blade set with internal cooling function is provided.Fig. 1 is the structural representation of the turbine blade set according to the embodiment of the present invention with internal cooling function.As shown in Figure 1, the turbine blade set that the present embodiment has an internal cooling function comprises: turbine blade body, heat exchanger, blower fan, gas compressor.Wherein, the present embodiment turbine blade body interior has cooling channel, in this cooling channel, adopts NH
3as cooling working medium.
Below respectively each constituent element of the present embodiment is described in detail.
In the present embodiment, turbine blade body is arranged in turbine casing, and the entrance of turbine casing is connected to firing chamber.The inside of turbine blade body has cooling channel.In this cooling channel, cooling working medium NH
3not only and between wall there is convection heat exchange, but also chemical reaction occur, absorb the heat of turbine blade wall:
2NH
3→N
2+3H
2
△H＝+46.2kJ/mol
In order to promote the carrying out of above-mentioned chemical reaction, the inwall of cooling channel is evenly coated with catalyzer.For cooling working medium NH
3, this catalyzer can be made up of MgO appendix active component Ni and other growth regulators.
The cold sender property outlet of heat exchanger is connected to the entrance of turbine blade internal cooling channel, and hot working fluid entrance is connected to the outlet of turbine blade internal cooling channel.The N of the high temperature come is transmitted by turbine blade internal cooling channel
2and H
2mixed gas, enter in this heat exchanger, under the environment of low temperature catalyst, heat-producing chemical reaction occur:
N
2+3H
2→2NH
3
△H＝-46.2kJ/mol
In order to promote the carrying out of above-mentioned chemical reaction, even coated catalysts on the inwall of heat exchanger.Wherein, this catalyzer can be: iron catalyst.
Wherein, the low temperature NH of generation
3mixed gas (mainly NH
3) to be entered by the outlet of heat exchanger cooling working medium and continue heat absorption in the cooling channel of turbine blade inside and decompose, so move in circles, realize the internal cooling to turbine blade.
The opposite side of heat exchanger is connected to gas compressor.This gas compressor provides Cryogenic air for heat exchanger, thus is the N of high temperature
2and H
2mixed gas cooling and provide low temperature environment for chemical reaction.
In addition, in order to realize circulating of cooling working medium, on the path of heat exchanger to turbine blade bulk transport cooling working medium, also blower fan is provided with.Wherein, low temperature NH
3mixed gas (mainly NH
3) enter gas flow in system in turbine blade power rely on small-sized fan carry out.
In this enforcement, circulating of adopting blower fan to be cooling working medium provides power, but the present invention is not as limit.In other embodiments of the invention, other mechanisms can also be adopted realize promotion cooling working medium to circulate.
Please refer to Fig. 1, below introduce the working procedure of the present embodiment turbine blade set: low temperature NH
3in the turbine blade internal cooling channel being covered with catalyzer, absorb the heat of blade interior wall, decompose, generate N
2and H
2; Reacted high-temperature gas mixture (mainly N
2and H
2) entering the heat exchanger that gas compressor place is covered with catalyzer, gas compressor heat exchanger opposite side is the Cryogenic air of gas compressor, after high-temperature synthesis gas is lowered the temperature by Cryogenic air, under the effect of catalyzer, synthesizes NH
3; Subsequently, low temperature NH
3mixed gas (mainly NH
3) power that relies on the power that provides of blower fan to enter gas flow in system in turbine blade relies on small-sized fan to carry out.
Those skilled in the art should find out: conventional air cooling is only inner at turbine blade, utilizes Cryogenic air to carry out convection heat exchange to high-temperature wall surface.And in the present embodiment, cooling working medium NH3 cooling air not only and there is convection heat exchange between wall, but also absorbs the heat of wall, there is following chemical reaction:
2NH
3——N
2+3H
2
△H＝+46.2kJ/mol
Compared to simple convection heat exchange, the cooling effectiveness of turbine blade inside clearly can be improved.
In addition, NH
3market price 6000 yuan/ton, economical and practical; Omnidistance sealing, capable of circulation, pollution-free, without dangerous, environment compatibility is good.
In a second embodiment of the present invention, a kind of gas turbine is additionally provided.Turbine blade set in this gas turbine application above-described embodiment.
It should be apparent to those skilled in the art that: due to the raising of turbine blade internal cooling efficiency, allow higher Turbine Inlet Gas Temperature, combustion gas is done work to be increased, and this can improve the thermal efficiency of gas turbine naturally; From blade high-temperature gas mixture out at synthesis NH
3process also to the Cryogenic air heat release in gas compressor, the temperature of firing chamber import high-pressure air is increased, contributes to fuel saving; NH
3the existence of cooling air decreases the cold gas from gas compressor for cooling turbine bucket, more cryogenic high pressure air can be made to enter combustion chambers burn acting, also contribute to improving the thermal efficiency.
So far, by reference to the accompanying drawings to invention has been detailed description.Describe according to above, the turbine blade set that those skilled in the art should have internal cooling function to the present invention and the gas turbine applying it have had clearly to be familiar with.
In addition, the above-mentioned definition to each element and method is not limited in various concrete structures, shape or the mode mentioned in embodiment, and those of ordinary skill in the art can change simply it or replace, such as:
(1) except gas compressor heat exchanger, the form of external cooling water can also be adopted, as long as the hot-fluid that synthetic ammonia can be made to produce dissipates;
(2) except the above-mentioned embodiment provided, can also be adopted other, the catalyzer of identical function can be realized, equally should within protection scope of the present invention.
In sum, the present invention has the turbine blade set of internal cooling function and applies its NH of gas turbine with gaseous state
3for cooling working medium cools turbine blade, cooling effectiveness is higher, also has the advantage that cost is low, environment compatibility is good simultaneously, has good application prospect.
Above-described specific embodiment; object of the present invention, technological scheme and beneficial effect are further described; be understood that; the foregoing is only specific embodiments of the invention; be not limited to the present invention; within the spirit and principles in the present invention all, any amendment made, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (10)
1. there is a turbine blade set for internal cooling function, it is characterized in that, comprising:
Turbine blade body, its inside has cooling channel, in this cooling channel, adopt NH
3as cooling working medium.
2. turbine blade set according to claim 1, is characterized in that, described cooling working medium NH
3the heat absorption of following chemical reaction is there is: 2NH in cooling channel
3→ N
2+ 3H
2.
3. turbine blade set according to claim 2, is characterized in that, the inwall coated catalysts of described cooling channel is with the above-mentioned chemical reaction of catalysis.
4. turbine blade set according to claim 3, is characterized in that, described catalyzer is made up of MgO appendix active component Ni and growth regulator.
5. turbine blade set according to claim 1, is characterized in that, also comprises:
Heat exchanger, its cold sender property outlet is connected to the entrance of turbine blade internal cooling channel, and hot working fluid entrance is connected to the outlet of turbine blade internal cooling channel;
Wherein, transmit by turbine blade internal cooling channel the N of coming
2and H
2mixed gas enter in heat exchanger, occur exothermic reaction: N
2+ 3H
2→ 2NH
3.
6. turbine blade set according to claim 5, is characterized in that, the inwall coated catalysts of described heat exchanger is with the above-mentioned chemical reaction of catalysis.
7. turbine blade set according to claim 6, is characterized in that, described catalyzer is iron catalyst.
8. turbine blade set according to claim 5, is characterized in that, also comprises:
Gas compressor, it is connected to described heat exchanger, for the N for entering heat exchanger inside
2and H
2mixed gas cooling and provide low temperature environment for the carrying out of above-mentioned exothermic reaction.
9. turbine blade set according to claim 5, is characterized in that, also comprises:
Blower fan, is connected between described turbine blade body and heat exchanger, for realizing cooling working medium circulating between.
10. a gas turbine, is characterized in that, application rights requires the turbine blade set according to any one of 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510204514.3A CN104832219B (en) | 2015-04-27 | 2015-04-27 | Turbine blade device with internal cooling function and gas turbine applying same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510204514.3A CN104832219B (en) | 2015-04-27 | 2015-04-27 | Turbine blade device with internal cooling function and gas turbine applying same |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104832219A true CN104832219A (en) | 2015-08-12 |
| CN104832219B CN104832219B (en) | 2017-01-18 |
Family
ID=53810360
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|---|---|---|---|
| CN201510204514.3A Active CN104832219B (en) | 2015-04-27 | 2015-04-27 | Turbine blade device with internal cooling function and gas turbine applying same |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105806873A (en) * | 2016-03-17 | 2016-07-27 | 上海发电设备成套设计研究院 | Cooling equal expansion ratio cooling effect test device of turbine blade of gas turbine |
| CN105806874A (en) * | 2016-03-17 | 2016-07-27 | 上海发电设备成套设计研究院 | Total-temperature equal expansion ratio cooling effect test device of turbine blade of gas turbine |
| US11920524B2 (en) | 2021-04-15 | 2024-03-05 | Rtx Corporation | Multi-fuel, fuel injection system for a turbine engine |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11859535B2 (en) | 2021-03-09 | 2024-01-02 | Rtx Corporation | Fuel-cooled engine component(s) |
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| GB931952A (en) * | 1959-09-04 | 1963-07-24 | Chemie Linz Ag | A process for utilizing the heat of expended gases from an exothermic gas synthesis |
| CN1632438A (en) * | 2004-12-22 | 2005-06-29 | 华南理工大学 | Amino thermochemical high temperature energy storage method and apparatus therefor |
| CN101832154A (en) * | 2009-03-11 | 2010-09-15 | 中国科学院工程热物理研究所 | Method for cooling air film of turbine blade of aircraft engine |
| CN102562310A (en) * | 2012-03-12 | 2012-07-11 | 云南大学 | Method for reducing temperature of high-temperature metal piece of gas turbine by ammonia decomposition catalysis reaction |
-
2015
- 2015-04-27 CN CN201510204514.3A patent/CN104832219B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB931952A (en) * | 1959-09-04 | 1963-07-24 | Chemie Linz Ag | A process for utilizing the heat of expended gases from an exothermic gas synthesis |
| CN1632438A (en) * | 2004-12-22 | 2005-06-29 | 华南理工大学 | Amino thermochemical high temperature energy storage method and apparatus therefor |
| CN101832154A (en) * | 2009-03-11 | 2010-09-15 | 中国科学院工程热物理研究所 | Method for cooling air film of turbine blade of aircraft engine |
| CN102562310A (en) * | 2012-03-12 | 2012-07-11 | 云南大学 | Method for reducing temperature of high-temperature metal piece of gas turbine by ammonia decomposition catalysis reaction |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105806873A (en) * | 2016-03-17 | 2016-07-27 | 上海发电设备成套设计研究院 | Cooling equal expansion ratio cooling effect test device of turbine blade of gas turbine |
| CN105806874A (en) * | 2016-03-17 | 2016-07-27 | 上海发电设备成套设计研究院 | Total-temperature equal expansion ratio cooling effect test device of turbine blade of gas turbine |
| CN105806874B (en) * | 2016-03-17 | 2018-05-11 | 上海发电设备成套设计研究院 | The cold effect experimental rig of the expansion ratios such as the full temperature of combustion engine turbine blade |
| CN105806873B (en) * | 2016-03-17 | 2018-12-11 | 上海发电设备成套设计研究院 | The cold effect experimental rigs of expansion ratios such as combustion engine turbine blade cooling |
| US11920524B2 (en) | 2021-04-15 | 2024-03-05 | Rtx Corporation | Multi-fuel, fuel injection system for a turbine engine |
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| Publication number | Publication date |
|---|---|
| CN104832219B (en) | 2017-01-18 |
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