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RU2012113194A - METHOD FOR INCREASING POWER AND KPD GAS TURBINE ENGINE - Google Patents

METHOD FOR INCREASING POWER AND KPD GAS TURBINE ENGINE Download PDF

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Publication number
RU2012113194A
RU2012113194A RU2012113194/06A RU2012113194A RU2012113194A RU 2012113194 A RU2012113194 A RU 2012113194A RU 2012113194/06 A RU2012113194/06 A RU 2012113194/06A RU 2012113194 A RU2012113194 A RU 2012113194A RU 2012113194 A RU2012113194 A RU 2012113194A
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RU
Russia
Prior art keywords
pressure compressor
combustion chamber
low
pressure
gas turbine
Prior art date
Application number
RU2012113194/06A
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Russian (ru)
Other versions
RU2499152C1 (en
Inventor
Андрей Викторович Кулеш
Мидхат Губайдуллович Хабибуллин
Марат Рашидович Латыпов
Михаил Викторович Додонов
Original Assignee
Открытое акционерное общество Конструкторско-производственное предприятие "Авиамотор"
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Priority to RU2012113194/06A priority Critical patent/RU2499152C1/en
Publication of RU2012113194A publication Critical patent/RU2012113194A/en
Application granted granted Critical
Publication of RU2499152C1 publication Critical patent/RU2499152C1/en

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Abstract

Способ повышения мощности и к.п.д. газотурбинного двигателя, содержащего компрессор низкого давления с турбиной низкого давления, компрессор высокого давления с турбиной высокого давления, камеру сгорания и опоры, путем подрезания верхней части лопаток компрессора низкого давления, отличающийся тем, что компрессор высокого давления и турбину высокого давления оборудуют дополнительными ступенями, а отношение длины камеры сгорания Lк ее исходной длине L выбирают в пределах 0,7÷0,79, при этом кольцевую жаровую трубу крепят к наружному корпусу камеры сгорания посредством кронштейна, выполненного в виде кольцевой детали.The way to increase power and efficiency a gas turbine engine comprising a low-pressure compressor with a low-pressure turbine, a high-pressure compressor with a high-pressure turbine, a combustion chamber and bearings, by cutting the upper part of the blades of the low-pressure compressor, characterized in that the high-pressure compressor and high-pressure turbine are equipped with additional stages, and the ratio of the length of the combustion chamber L to its initial length L is selected within 0.7 ÷ 0.79, while the annular flame tube is attached to the outer casing of the combustion chamber by means of matte formed as a ring component.

Claims (1)

Способ повышения мощности и к.п.д. газотурбинного двигателя, содержащего компрессор низкого давления с турбиной низкого давления, компрессор высокого давления с турбиной высокого давления, камеру сгорания и опоры, путем подрезания верхней части лопаток компрессора низкого давления, отличающийся тем, что компрессор высокого давления и турбину высокого давления оборудуют дополнительными ступенями, а отношение длины камеры сгорания L1 к ее исходной длине L выбирают в пределах 0,7÷0,79, при этом кольцевую жаровую трубу крепят к наружному корпусу камеры сгорания посредством кронштейна, выполненного в виде кольцевой детали. The way to increase power and efficiency a gas turbine engine comprising a low-pressure compressor with a low-pressure turbine, a high-pressure compressor with a high-pressure turbine, a combustion chamber and bearings, by cutting the upper part of the blades of the low-pressure compressor, characterized in that the high-pressure compressor and high-pressure turbine are equipped with additional stages, and the ratio of the length of the combustion chamber L 1 to its initial length L is selected within 0.7 ÷ 0.79, while the annular flame tube is attached to the outer casing of the combustion chamber by cr on the bracket made in the form of an annular part.
RU2012113194/06A 2012-04-04 2012-04-04 Method of bypass turbojet conversion into ground-based gas turbine engine RU2499152C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU2012113194/06A RU2499152C1 (en) 2012-04-04 2012-04-04 Method of bypass turbojet conversion into ground-based gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU2012113194/06A RU2499152C1 (en) 2012-04-04 2012-04-04 Method of bypass turbojet conversion into ground-based gas turbine engine

Publications (2)

Publication Number Publication Date
RU2012113194A true RU2012113194A (en) 2013-10-10
RU2499152C1 RU2499152C1 (en) 2013-11-20

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Family Applications (1)

Application Number Title Priority Date Filing Date
RU2012113194/06A RU2499152C1 (en) 2012-04-04 2012-04-04 Method of bypass turbojet conversion into ground-based gas turbine engine

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Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IL228274A (en) * 2013-09-03 2016-10-31 Israel Aerospace Ind Ltd Turbofan engine and method for converting a turbofan engine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2405919A (en) * 1940-03-02 1946-08-13 Power Jets Res & Dev Ltd Fluid flow energy transformer
US3677012A (en) * 1962-05-31 1972-07-18 Gen Electric Composite cycle turbomachinery
SU1726812A1 (en) * 1989-07-26 1992-04-15 Уфимский авиационный институт им.Серго Орджоникидзе Method of converting two aircraft engines into compressor plant
RU2305789C2 (en) * 2005-08-22 2007-09-10 Открытое акционерное общество "Авиадвигатель" Gas-turbine plant

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Publication number Publication date
RU2499152C1 (en) 2013-11-20

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MM4A The patent is invalid due to non-payment of fees

Effective date: 20140405