CN1323225C - Method for changing turbine fan engine into industrial combustion machine - Google Patents
Method for changing turbine fan engine into industrial combustion machine Download PDFInfo
- Publication number
- CN1323225C CN1323225C CNB031337457A CN03133745A CN1323225C CN 1323225 C CN1323225 C CN 1323225C CN B031337457 A CNB031337457 A CN B031337457A CN 03133745 A CN03133745 A CN 03133745A CN 1323225 C CN1323225 C CN 1323225C
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- CN
- China
- Prior art keywords
- casing
- industrial combustion
- combustion machine
- turbofan engine
- intermediary
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The present invention relates to a method for reforming a turbofan engine into an industrial combustion engine, which aims to overcome the defects of difficult reform and large investment in the existing method. On the basis of the existing turbofan engine, front spacing rings and back spacing rings are respectively arranged at the front installation edges and the back installation edges of an air inlet case and an intermediate case, and the adjacent parts of the rings are connected by tenons so as to reduce flow path passages and meet requirements of engine types after reform.
Description
Affiliated technical field
The present invention relates to a kind of method of utilizing turbofan engine to change system into industrial combustion machine.
Background technique
Utilizing turbofan engine to repack industrial combustion machine into often needs fan to cut the top, dwindle the meridian plane flow process passage of low pressure compressor, inlet guide vane in the transformation of the way inlet casing and the support plate in intermediary's casing, it is big to run into transformation of the way difficulty in the practice, technological process is long, the input tooling device is many, the cost height.
Summary of the invention
To utilize existing turbofan engine to change system into industrial combustion machine difficulty big in order to overcome, and technological process is long, the deficiency that restructuring cost is high, the present invention will provide a kind of turbofan engine that utilizes, and little investment is set up simple in structure, easily assembly just can easily be changed system into industrial combustion machine.
The technical solution adopted for the present invention to solve the technical problems is on the basis of former turbofan engine main body, for reaching the purpose of the meridian plane flow process passage that dwindles low pressure compressor, the preceding installation limit of the inlet casing among the Yu Yuanji and intermediary's casing is respectively equipped with front split ring; The back is installed the limit and is respectively equipped with rear split ring, and the adjacent portions group of forward and backward spacer ring is a joggle.
The invention has the beneficial effects as follows: utilize turbofan engine to repack industrial combustion machine into, reach the purpose of dwindling the flow process passage to install front and back spacer ring simple in structure additional, avoid again inlet casing and intermediary's casing of manufacturing structure complexity, shorten the reforming technology flow process, reduce the tooling device investment, and save a large amount of transformations of the way, recondition expense.
Description of drawings
The present invention is further described below in conjunction with drawings and Examples.
Fig. 1 is that inlet casing of the present invention is set up forward and backward spacer ring structural representation;
Fig. 2 is that intermediary of the present invention casing is set up forward and backward ring structure schematic representation.
Among the figure, limit, 2 inlet casing front split rings, 3 inlet casings are installed before 1 inlet casing, behind 4 inlet casings limit is installed, limit, 7 intermediary's casing front split rings are installed before the 5 inlet casing rear split rings, 6 intermediary's casings, 8 intermediary's casings are installed the limit behind 9 intermediary's casings, 10 intermediary's casing rear split rings.
Embodiment
By Fig. 1-2 as can be known, the present invention adopts the industry combustion machine that turbofan engine changes system into, and it is to be provided with front split ring 2 in that limit 1 was installed before inlet casing 3 on the basis of turbofan engine, and the back is installed limit 4 and is provided with rear split ring 5; Before intermediary's casing 8 limit 6 is installed and is provided with front split ring 7, the back is installed limit 9 and is provided with rear split ring 10, the adjacent portions group of the front and back spacer ring on inlet casing 3 and the intermediary's casing 8 is a joggle, inlet casing and intermediary's casing flow process passage reduction volume can be determined as required, dwindle 15～30% as inlet casing flow process passage, intermediary's casing flow process passage dwindles 10～25%.
Claims (1)
1, a kind of method of utilizing turbofan engine to change system into industrial combustion machine, adopt the turbofan engine main body, it is characterized in that installing the limit and be respectively equipped with front split ring before inlet casing and intermediary's casing, the back is installed the limit and is respectively equipped with rear split ring, and the adjacent portions group is a joggle between the spacer ring of front and back.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031337457A CN1323225C (en) | 2003-07-16 | 2003-07-16 | Method for changing turbine fan engine into industrial combustion machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB031337457A CN1323225C (en) | 2003-07-16 | 2003-07-16 | Method for changing turbine fan engine into industrial combustion machine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1474039A CN1474039A (en) | 2004-02-11 |
| CN1323225C true CN1323225C (en) | 2007-06-27 |
Family
ID=34154323
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB031337457A Expired - Fee Related CN1323225C (en) | 2003-07-16 | 2003-07-16 | Method for changing turbine fan engine into industrial combustion machine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1323225C (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105484871B (en) * | 2015-11-23 | 2017-05-24 | 沈阳黎明航空发动机(集团)有限责任公司 | Vehicle-mounted gas turbine transformed from obsolete fanjet |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4759687A (en) * | 1986-04-24 | 1988-07-26 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Turbine ring incorporating elements of a ceramic composition divided into sectors |
| US4781530A (en) * | 1986-07-28 | 1988-11-01 | Cummins Engine Company, Inc. | Compressor range improvement means |
| US4990053A (en) * | 1988-06-29 | 1991-02-05 | Asea Brown Boveri Ltd. | Device for extending the performances of a radial compressor |
| CN1052169A (en) * | 1989-11-21 | 1991-06-12 | 北京市西城新开通用试验厂 | A kind of aircraft turbine engine used as ground power apparatus |
| US5137419A (en) * | 1984-06-19 | 1992-08-11 | Rolls-Royce Plc | Axial flow compressor surge margin improvement |
| US5236301A (en) * | 1991-12-23 | 1993-08-17 | Allied-Signal Inc. | Centrifugal compressor |
| CN1096347A (en) * | 1993-03-04 | 1994-12-14 | Abb管理有限公司 | Has the centrifugal compressor that can make the stable casing that flows |
| CN1107546A (en) * | 1993-09-03 | 1995-08-30 | Abb管理有限公司 | Method and appliance for matching the radial turbine of a turbocharger to an internal combustion engine |
| US5961278A (en) * | 1997-12-17 | 1999-10-05 | Pratt & Whitney Canada Inc. | Housing for turbine assembly |
| CN1281953A (en) * | 1999-07-15 | 2001-01-31 | 株式会社日立制作所 | Turbomachine |
-
2003
- 2003-07-16 CN CNB031337457A patent/CN1323225C/en not_active Expired - Fee Related
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5137419A (en) * | 1984-06-19 | 1992-08-11 | Rolls-Royce Plc | Axial flow compressor surge margin improvement |
| US4759687A (en) * | 1986-04-24 | 1988-07-26 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Turbine ring incorporating elements of a ceramic composition divided into sectors |
| US4781530A (en) * | 1986-07-28 | 1988-11-01 | Cummins Engine Company, Inc. | Compressor range improvement means |
| US4990053A (en) * | 1988-06-29 | 1991-02-05 | Asea Brown Boveri Ltd. | Device for extending the performances of a radial compressor |
| CN1052169A (en) * | 1989-11-21 | 1991-06-12 | 北京市西城新开通用试验厂 | A kind of aircraft turbine engine used as ground power apparatus |
| US5236301A (en) * | 1991-12-23 | 1993-08-17 | Allied-Signal Inc. | Centrifugal compressor |
| CN1096347A (en) * | 1993-03-04 | 1994-12-14 | Abb管理有限公司 | Has the centrifugal compressor that can make the stable casing that flows |
| CN1107546A (en) * | 1993-09-03 | 1995-08-30 | Abb管理有限公司 | Method and appliance for matching the radial turbine of a turbocharger to an internal combustion engine |
| US5961278A (en) * | 1997-12-17 | 1999-10-05 | Pratt & Whitney Canada Inc. | Housing for turbine assembly |
| CN1281953A (en) * | 1999-07-15 | 2001-01-31 | 株式会社日立制作所 | Turbomachine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1474039A (en) | 2004-02-11 |
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|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20070627 Termination date: 20160716 |
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| CF01 | Termination of patent right due to non-payment of annual fee |