RU2011137364A - COMPRESSOR-TURBINE ENGINE WITH TRANSVERSE LOCATION OF STEPS OF A GAS TURBINE - Google Patents
COMPRESSOR-TURBINE ENGINE WITH TRANSVERSE LOCATION OF STEPS OF A GAS TURBINE Download PDFInfo
- Publication number
- RU2011137364A RU2011137364A RU2011137364/06A RU2011137364A RU2011137364A RU 2011137364 A RU2011137364 A RU 2011137364A RU 2011137364/06 A RU2011137364/06 A RU 2011137364/06A RU 2011137364 A RU2011137364 A RU 2011137364A RU 2011137364 A RU2011137364 A RU 2011137364A
- Authority
- RU
- Russia
- Prior art keywords
- gas turbine
- compressor
- axis
- prsgt
- ktad
- Prior art date
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Abstract
1. Компрессорно-турбинный авиационный двигатель с поперечным расположением ступеней газовой турбины (КТАД с ПРСГТ), включающий в себя: входное устройство, компрессор, противоточную камеру сгорания, газовую турбину, реактивное сопло, редуктор, отличающийся тем, что камера сгорания расположена по оси двигателя в центре конструкции.2. КТАД с ПРСГТ по п.1, отличающийся тем, что выработка мощности для вращения компрессора происходит на двух ступенях газовой турбины, расположенных по разные стороны от оси двигателя и связанные единым валом, расположенным перпендикулярно к оси вала компрессора, возникающие силы не влияют на значение осевой силы (тяги), создаваемой компрессором.3. КТАД с ПРСГТ по п.1, отличающийся тем, что используемая для привода компрессора газовая турбина с расположенными по разные стороны от оси ступенями, размещена горизонтально по отношению к строительной оси воздушного судна, с обратным подводом рабочего тела (газа) к одной (нижней) из ступеней газовой турбины, суммарная сила, возникающая при обтекании рабочим телом (газом) лопаток газовой турбины создает дополнительную подъемную силу.4. КТАД с ПРСГТ по п.1, отличающийся тем, что поперечное расположение газовой турбины сокращает длину двигателя и соответственно уменьшает его массу, за счет уменьшения длины вала.5. КТАД с ПРСГТ по п.1, отличающийся тем, что расположенная по оси двигателя камера сгорания имеет значительно меньшую массу, за счет уменьшения ее объема.1. A compressor-turbine aircraft engine with a transverse gas turbine stage (KTAD with PRSGT), including: an input device, a compressor, a counter-flow combustion chamber, a gas turbine, a jet nozzle, a gearbox, characterized in that the combustion chamber is located along the axis of the engine in the center of the structure. 2. KTAD with PRSGT according to claim 1, characterized in that the power generation for compressor rotation occurs at two stages of the gas turbine located on opposite sides of the engine axis and connected by a single shaft located perpendicular to the axis of the compressor shaft, the forces arising do not affect the axial value force (traction) generated by the compressor. 3. KTAD with PRSGT according to claim 1, characterized in that the gas turbine used to drive the compressor with steps located on opposite sides of the axis is placed horizontally with respect to the aircraft construction axis, with the working fluid (gas) back fed to one (lower) from the steps of a gas turbine, the total force arising when the blades of a gas turbine flow around a working fluid (gas) creates additional lifting force. 4. KTAD with PRSGT according to claim 1, characterized in that the transverse arrangement of the gas turbine reduces the length of the engine and, accordingly, reduces its mass, by reducing the length of the shaft. KTAD with PRSGT according to claim 1, characterized in that the combustion chamber located along the axis of the engine has a significantly lower mass due to a decrease in its volume.
Claims (5)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2011137364/06A RU2533285C2 (en) | 2011-09-09 | 2011-09-09 | Compressor-turbine engine with crosswise arrangement of gas turbine stages |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
RU2011137364/06A RU2533285C2 (en) | 2011-09-09 | 2011-09-09 | Compressor-turbine engine with crosswise arrangement of gas turbine stages |
Publications (2)
Publication Number | Publication Date |
---|---|
RU2011137364A true RU2011137364A (en) | 2013-03-20 |
RU2533285C2 RU2533285C2 (en) | 2014-11-20 |
Family
ID=49123422
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
RU2011137364/06A RU2533285C2 (en) | 2011-09-09 | 2011-09-09 | Compressor-turbine engine with crosswise arrangement of gas turbine stages |
Country Status (1)
Country | Link |
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RU (1) | RU2533285C2 (en) |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
SU47508A1 (en) * | 1935-11-21 | 1936-06-30 | Е.В. Кюн | Internal combustion turbine |
GB1024969A (en) * | 1964-09-14 | 1966-04-06 | Rolls Royce | Helicopter power plant |
JPH07301150A (en) * | 1994-05-06 | 1995-11-14 | Isamu Nemoto | Cross compound turbofan |
RU2127818C1 (en) * | 1996-07-25 | 1999-03-20 | Пухлик Илья Борисович | Intershaft combustion turbine engine |
RU2272926C1 (en) * | 2005-05-31 | 2006-03-27 | Закрытое акционерное общество Научно-методический центр "Норма" (ЗАО НМЦ "Норма") | Hybrid jet engine |
-
2011
- 2011-09-09 RU RU2011137364/06A patent/RU2533285C2/en not_active IP Right Cessation
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Publication number | Publication date |
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RU2533285C2 (en) | 2014-11-20 |
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Legal Events
Date | Code | Title | Description |
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FA92 | Acknowledgement of application withdrawn (lack of supplementary materials submitted) |
Effective date: 20140320 |
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FZ9A | Application not withdrawn (correction of the notice of withdrawal) |
Effective date: 20140520 |
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HE9A | Changing address for correspondence with an applicant | ||
MM4A | The patent is invalid due to non-payment of fees |
Effective date: 20170910 |