CN104234859A - Fuel cover for gas turbine starter and production method thereof - Google Patents
Fuel cover for gas turbine starter and production method thereof Download PDFInfo
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- CN104234859A CN104234859A CN201310226182.XA CN201310226182A CN104234859A CN 104234859 A CN104234859 A CN 104234859A CN 201310226182 A CN201310226182 A CN 201310226182A CN 104234859 A CN104234859 A CN 104234859A
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- oil duct
- processing
- fuel cover
- oil way
- duct liner
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Abstract
The invention relates to a fuel cover for a gas turbine starter and a production method thereof. The fuel cover comprises an oil way inner bushing, and an oil way outer bushing covering the periphery of the oil way inner bushing and welded with the outer wall of the oil way inner bushing, wherein a boron nitride layer is sprayed on the inner side wall of the oil way inner bushing; in the prior art, the inner side of the oil way inner bushing needs to adopt a sealing layer, and the sealing layer is required to be processed by high temperature and high pressure, so that the processing is complex; and after the processing is changed to the surface spraying, the processing precision is reduced, the basic industry processing is more facilitated, the pass percent of products is improved, the production requirements are satisfied, and the cost is reduced. A three-layer structure of a conditional fuel cover is changed to a two-layer structure through structural improvement, so that the structure and the processing technology are simplified, the weight is reduced, the production processing is facilitated, and the pass percent of the products is largely improved; and the processing technology can guarantee no entrance of a spaying material into a through hole in the oil way inner bushing, so that the design requirement is satisfied, and the technology is simple.
Description
Technical field
The present invention relates to a kind of gas turbine starter (particularly mini engine) fuel cover and manufacture method thereof.
Background technique
Fuel cover of the present invention is used on certain type gas turbine starter, belongs to one of important spare part in combustion system, for providing jet flow fuel oil when gas turbine starter works.
Fuel cover is the assembly parts of the many weld parts of multilayer, there are gas circuit, oil circuit in the inside of fuel cover, sleeve surface is sprayed with seal coating, seal coating needs High Temperature High Pressure to process, structure is relatively complicated, add that the little difficulty of processing of part geometry size is large, and processing needs high-precision specialized factory, conforming product rate is very low.
Fuel cover is the flow fuel oil providing spray angle to firing chamber, and also will carry out sealing simultaneously and ensure that in firing chamber, high-temperature high-pressure fuel gas can not leak from dynamic slit, therefore, fuel cover is a vitals, and its quality directly affects combustion efficiency.
Summary of the invention
Technical problem to be solved by this invention is to provide a kind of gas turbine starter fuel cover and manufacture method thereof, and this fuel cover difficulty of processing is little, simple and compact for structure, and lighter in weight, adds man-hour conforming product rate higher.
For solving the problems of the technologies described above, the invention provides a kind of gas turbine starter fuel cover, comprising: oil duct liner road, be set in this periphery, oil duct liner road and the oil duct external bushing welded with its outer wall; The madial wall in described oil duct liner road is coated with boron nitride layer; In prior art, the inner side of oil duct neck bush needs to adopt sealing layer, and sealing layer needs, with High Temperature High Pressure processing, to process loaded down with trivial details, after changing surface spraying into, reduce machining accuracy, be more suitable for basic industry processing, the more important thing is the up-to-standard rate improving product, meet need of production, save cost.
The inside diameter surface in described oil duct liner road has multiple through hole with circle distribution, for cooling fuel cover by air-flow.
The manufacture method of above-mentioned gas turbine starter fuel cover, in turn includes the following steps:
A. the processing in oil duct liner road 11: be provided with a circle annular boss in prefabricated oil duct liner road, the outer circumferential face in oil duct liner road offers multiple circular half bore corresponding with the position of this annular boss with circumference;
B. oil duct external bushing is set in periphery, oil duct liner road and be welded and fixed;
C. at liner road internal surface spraying boron nitride layer, thickness is 0.5-1mm;
D. press annular boss described in predefined value turning, and make circular half bore become through hole, thus ensure can not enter sprayed on material in through hole.
Technique effect of the present invention: the present invention, by architecture advances, makes two-layer structure into the three-decker of existing fuel cover, simplifies the structure with processing technology, alleviates weight, be beneficial to production and processing, increased substantially conforming product rate; The inner side of oil duct neck bush of the prior art needs to adopt sealing layer, and sealing layer needs, with High Temperature High Pressure processing, to process loaded down with trivial details; The present invention is by the improvement of oil duct liner road processing technology, thus spraying can be realized smoothly, after spraying boron nitride layer, the combination force of sprayfused coating and sprayed surface is increased, reduce requirement on machining accuracy, be more suitable for basic industry processing, through actual verification, spraying boron nitride difficult drop-off, and meet sealing use and life requirements, and improve conforming product rate, meet need of production, save cost; The processing technology that the present invention adopts, can ensure can not enter sprayed on material in the through hole on oil duct liner road, avoid the situation occurring that through hole blocks, and avoids the impurity that there is sprayed on material production in relevant oil circuit, gas circuit simultaneously; Meet designing requirement, and technique is simple.
Accompanying drawing explanation
Below in conjunction with specific embodiment, the present invention is described in further detail:
Fig. 1 is the structural representation of gas turbine starter fuel cover of the present invention;
Fig. 2 is the F-F partial sectional view of Fig. 1
Fig. 3 is that oil duct liner road partly cuts open schematic diagram;
Fig. 4 is the C-C oil duct liner road partial sectional view of Fig. 3.
Embodiment
As Fig. 1, the gas turbine starter fuel cover of the present embodiment, comprising: oil duct liner road 11, is set in this oil duct liner periphery, road 11 and the oil duct external bushing 12 welded with its outer wall; The madial wall in described oil duct liner road 11 is coated with boron nitride layer 2.
The inside diameter surface in described oil duct liner road 11 has the through hole 21 of multiple φ 3 with circle distribution.
As Fig. 1-4, the manufacture method of above-mentioned gas turbine starter fuel cover, it in turn includes the following steps:
A. the processing in oil duct liner road 11: be provided with a circle width w=4mm in prefabricated oil duct liner road, the annular boss 23 of height h=5mm, the outer circumferential face in oil duct liner road 11 offers 19 Φ 3 circular half bore 210,19 circular half bore corresponding with the position of this annular boss 23 210 by the uniform mode adjacent distributions in 24 holes with circumference;
B. oil duct external bushing 12 is set in oil duct liner periphery, road 11 and be welded and fixed;
C. at liner road internal surface spraying boron nitride layer 2, thickness is 0.7mm;
D. by annular boss described in predefined value turning (such as: to be pruned by described annular boss 4mm in the short transverse of described annular boss), and make circular half bore 210 become through hole 21, thus ensure can not enter sprayed on material in circular hole.
Obviously, above-described embodiment is only for example of the present invention is clearly described, and is not the restriction to embodiments of the present invention.For those of ordinary skill in the field, can also make other changes in different forms on the basis of the above description.Here exhaustive without the need to also giving all mode of executions.And these belong to spirit institute's apparent change of extending out of the present invention or change and are still among protection scope of the present invention.
Claims (3)
1. a gas turbine starter fuel cover, is characterized in that comprising: oil duct liner road, is set in this periphery, oil duct liner road and the oil duct external bushing welded with its outer wall; The madial wall in described oil duct liner road is coated with boron nitride layer.
2. gas turbine starter fuel cover as claimed in claim 1, is characterized in that: the inside diameter surface in described oil duct liner road has multiple through hole with circle distribution.
3. the manufacture method of gas turbine starter fuel cover as claimed in claim 2, is characterized in that: this manufacture method in turn includes the following steps:
A. the processing in oil duct liner road: be provided with a circle annular boss in prefabricated oil duct liner road, the outer circumferential face in oil duct liner road offers multiple circular half bore corresponding with the position of this annular boss with circumference;
B. oil duct external bushing is set in periphery, oil duct liner road and be welded and fixed;
C. at liner road internal surface spraying boron nitride layer, thickness is 0.5-1mm;
D. press annular boss described in predefined value turning, and make circular half bore become described through hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310226182.XA CN104234859B (en) | 2013-06-07 | 2013-06-07 | A kind of manufacture method of gas turbine starter fuel cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310226182.XA CN104234859B (en) | 2013-06-07 | 2013-06-07 | A kind of manufacture method of gas turbine starter fuel cover |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104234859A true CN104234859A (en) | 2014-12-24 |
| CN104234859B CN104234859B (en) | 2016-08-31 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310226182.XA Active CN104234859B (en) | 2013-06-07 | 2013-06-07 | A kind of manufacture method of gas turbine starter fuel cover |
Country Status (1)
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| CN (1) | CN104234859B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106415133A (en) * | 2014-06-02 | 2017-02-15 | 索拉透平公司 | Combustor assembly for a gas turbine engine having a braze layer having a centerline eutectic free region |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5003767A (en) * | 1988-03-25 | 1991-04-02 | Sundstrand Corporation | Gas turbine starter system with power augmentation |
| CN1221067A (en) * | 1997-11-26 | 1999-06-30 | 联合技术公司 | Columnar zirconium oxide abrasive coating for gas turbine engine seal system |
| CN1268215A (en) * | 1997-09-18 | 2000-09-27 | 西门子公司 | Adapter armature for use in a stationary gas turbine installation |
| CN1828140A (en) * | 2005-03-02 | 2006-09-06 | 通用电气公司 | One-piece can combustor |
| CN102889616A (en) * | 2012-09-29 | 2013-01-23 | 中国科学院工程热物理研究所 | Multi-point direct spray combustion chamber based on venturi premixing double spiral nozzle |
| CN203296945U (en) * | 2013-06-07 | 2013-11-20 | 常州兰翔机械有限责任公司 | Fuel oil cover for gas turbine starter |
-
2013
- 2013-06-07 CN CN201310226182.XA patent/CN104234859B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5003767A (en) * | 1988-03-25 | 1991-04-02 | Sundstrand Corporation | Gas turbine starter system with power augmentation |
| CN1268215A (en) * | 1997-09-18 | 2000-09-27 | 西门子公司 | Adapter armature for use in a stationary gas turbine installation |
| CN1221067A (en) * | 1997-11-26 | 1999-06-30 | 联合技术公司 | Columnar zirconium oxide abrasive coating for gas turbine engine seal system |
| CN1828140A (en) * | 2005-03-02 | 2006-09-06 | 通用电气公司 | One-piece can combustor |
| CN102889616A (en) * | 2012-09-29 | 2013-01-23 | 中国科学院工程热物理研究所 | Multi-point direct spray combustion chamber based on venturi premixing double spiral nozzle |
| CN203296945U (en) * | 2013-06-07 | 2013-11-20 | 常州兰翔机械有限责任公司 | Fuel oil cover for gas turbine starter |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106415133A (en) * | 2014-06-02 | 2017-02-15 | 索拉透平公司 | Combustor assembly for a gas turbine engine having a braze layer having a centerline eutectic free region |
| CN106415133B (en) * | 2014-06-02 | 2019-08-30 | 索拉透平公司 | Gas-turbine unit burner assembly with the brazing layer with center line without eutectic area |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104234859B (en) | 2016-08-31 |
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