ES2342586B1 - Turbopropulsor aeronautico. - Google Patents
Turbopropulsor aeronautico. Download PDFInfo
- Publication number
- ES2342586B1 ES2342586B1 ES200801317A ES200801317A ES2342586B1 ES 2342586 B1 ES2342586 B1 ES 2342586B1 ES 200801317 A ES200801317 A ES 200801317A ES 200801317 A ES200801317 A ES 200801317A ES 2342586 B1 ES2342586 B1 ES 2342586B1
- Authority
- ES
- Spain
- Prior art keywords
- turbine
- turboprop
- low pressure
- combustion chamber
- high pressure
- 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
Links
- 238000002485 combustion reaction Methods 0.000 claims abstract description 45
- 239000007789 gas Substances 0.000 claims abstract description 22
- 239000007800 oxidant agent Substances 0.000 claims abstract description 18
- 239000000446 fuel Substances 0.000 claims abstract description 17
- 239000000203 mixture Substances 0.000 claims abstract description 16
- 230000001590 oxidative effect Effects 0.000 claims abstract description 15
- 230000002093 peripheral effect Effects 0.000 claims abstract description 7
- 230000006835 compression Effects 0.000 claims description 8
- 238000007906 compression Methods 0.000 claims description 8
- CBENFWSGALASAD-UHFFFAOYSA-N Ozone Chemical compound [O-][O+]=O CBENFWSGALASAD-UHFFFAOYSA-N 0.000 claims description 7
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 3
- 239000001301 oxygen Substances 0.000 claims description 3
- 229910052760 oxygen Inorganic materials 0.000 claims description 3
- 238000006243 chemical reaction Methods 0.000 abstract description 5
- 238000010276 construction Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 4
- 238000005057 refrigeration Methods 0.000 description 3
- 239000000243 solution Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 238000012423 maintenance Methods 0.000 description 2
- 230000003319 supportive effect Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 235000013399 edible fruits Nutrition 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/065—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front and aft fans
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
- -
- La mezcla de combustible y oxidante no es uniforme cuando se produce la reacción, con lo cual la combustión no es óptima, en especial debido a diferentes concentraciones relativas de ambos en el volumen de la cámara.
- -
- A consecuencia de ello, los gases no son entregados a la turbina con una temperatura uniforme, si no que el perfil de temperaturas de éstos presenta máximos y mínimos, que resultan en mayores tensiones térmicas en los álabes del rotor y del estator, requiriendo de éstos mayores límites de resistencia y por lo tanto mayores costes.
- -
- El control de la potencia se realiza con el único parámetro de la inyección de combustible, cuya adaptación a las diferentes condiciones de altura no es óptima, puesto que las concentraciones de oxígeno dependen de la altura.
\vskip1.000000\baselineskip
- -
- Es de construcción compacta,
- -
- No se necesitan tantas etapas como en las turbinas convencionales, las cuales pueden llegar a necesitar hasta seis discos de álabes, y por lo tanto tiene un peso menor,
- -
- Los álabes de salida se pueden diseñar para que gire a la velocidad óptima,
- -
- Tiene pocas piezas y es de fácil mantenimiento,
- -
- Implica un consumo de energía global menor.
- -
- No se necesita una caja de engranajes para reducir la alta velocidad del eje central, puesto que esta turbina gira independientemente de éste.
- -
- el compresor de baja presión,
- -
- la primera sección del compresor de alta presión,
- -
- la segunda sección del compresor de alta presión,
- -
- la segunda turbina de alta presión, la primera turbina de alta presión,
- -
- la segunda turbina de baja presión,
- -
- la entrada a la turbina de baja presión,
- -
- la salida de la turbina de baja presión.
\vskip1.000000\baselineskip
Claims (16)
- -
- el compresor de baja presión (16),
- -
- la primera sección del compresor de alta presión (18),
- -
- la segunda sección del compresor de alta presión (21),
- -
- la segunda turbina de alta presión (23), la primera turbina de alta presión (15),
- -
- la segunda turbina de baja presión (27),
- -
- la entrada (12) a la turbina de baja presión (8),
- -
- la salida (26) de la turbina de baja presión (8).
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
ES200801317A ES2342586B1 (es) | 2008-04-30 | 2008-04-30 | Turbopropulsor aeronautico. |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
ES200801317A ES2342586B1 (es) | 2008-04-30 | 2008-04-30 | Turbopropulsor aeronautico. |
Publications (2)
Publication Number | Publication Date |
---|---|
ES2342586A1 ES2342586A1 (es) | 2010-07-08 |
ES2342586B1 true ES2342586B1 (es) | 2011-06-14 |
Family
ID=42272324
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
ES200801317A Expired - Fee Related ES2342586B1 (es) | 2008-04-30 | 2008-04-30 | Turbopropulsor aeronautico. |
Country Status (1)
Country | Link |
---|---|
ES (1) | ES2342586B1 (es) |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1321657A (en) * | 1970-09-16 | 1973-06-27 | Secr Defence | Ducted fan gas turbine jet propulsion engine |
GB2189844A (en) * | 1986-04-30 | 1987-11-04 | Rolls Royce | Gas turbine engines |
FR2645911B1 (fr) * | 1989-04-18 | 1991-06-07 | Snecma | Moteur a grand taux de dilution a soufflante amont et soufflante aval |
DE19749648A1 (de) * | 1997-11-10 | 1999-05-12 | Gerhard Ittner | Zweistufiger Verdichter für Turbinen Überhyperschalltriebwerk |
US7788899B2 (en) * | 2005-12-29 | 2010-09-07 | United Technologies Corporation | Fixed nozzle thrust augmentation system |
-
2008
- 2008-04-30 ES ES200801317A patent/ES2342586B1/es not_active Expired - Fee Related
Also Published As
Publication number | Publication date |
---|---|
ES2342586A1 (es) | 2010-07-08 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
EC2A | Search report published |
Date of ref document: 20100708 Kind code of ref document: A1 |
|
FG2A | Definitive protection |
Ref document number: 2342586 Country of ref document: ES Kind code of ref document: B1 Effective date: 20110614 |
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PC2A | Transfer of patent |
Owner name: JOSE LUIS BECERRIL RUIZ Effective date: 20130503 |
|
PC2A | Transfer of patent |
Owner name: JOSE ANTONIO JALDO ROPERO Effective date: 20130507 |
|
PC2A | Transfer of patent |
Owner name: AERO ENGINEERING, S.L. Effective date: 20130619 |
|
FD2A | Announcement of lapse in spain |
Effective date: 20210928 |