CN107091162B - Power turbine adjustable engine - Google Patents
Power turbine adjustable engine Download PDFInfo
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- CN107091162B CN107091162B CN201710318415.7A CN201710318415A CN107091162B CN 107091162 B CN107091162 B CN 107091162B CN 201710318415 A CN201710318415 A CN 201710318415A CN 107091162 B CN107091162 B CN 107091162B
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- Prior art keywords
- engine
- power turbine
- gas
- turbine
- rotating speed
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/16—Control of working fluid flow
- F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/02—Purpose of the control system to control rotational speed (n)
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
Abstract
The invention discloses a power turbine adjustable engine, which is provided with an air bleeding device used for adjusting the working capacity of a power turbine between a gas turbine and the power turbine. When the working capacity of the power turbine needs to be reduced, the air bleeding device is opened, and a part of gas is released, so that the gas entering the power turbine is reduced, the working capacity of the power turbine is reduced, and when the load is constant and the state of the gas generator is unchanged, the rotating speed of the power turbine is reduced, so that on one hand, the safety margin requirement of the critical rotating speed of the power turbine is met, and the waste of fuel oil caused by the fact that the requirement is met in a mode of improving the slow rotating speed of the gas generator is avoided; on the other hand, when the engine load is switched from the state of not being driven by the engine to the state of being driven by the engine, the heat generation of the clutch is reduced in the process of increasing the load rotating speed, and the working performance and the service life of the clutch are improved.
Description
Technical Field
The invention relates to the field of gas turbine engines, in particular to a power turbine adjustable engine.
Background
In the conventional gas turbine engine, the low-pressure turbine and the turbine in front of the low-pressure turbine are generally designed continuously according to the flow rate, so that for the power type gas turbine engine, when the environmental condition is constant, the working capacity of the low-pressure turbine used as the power turbine is determined by the working state of the gas generator, and if the environmental condition and the working state of the gas generator are not changed, the working capacity of the power turbine is not changed, the relation between the output torque and the output rotating speed of the power turbine is not changed, and the power turbine cannot be independently adjusted.
The design of continuous flow is sometimes not favorable for the design of the slow-running state of the turboshaft engine and the turboprop engine. Taking a turboshaft engine as an example, after the slow-moving state of a gas generator is designed according to conventional requirements, the working capacity of a power turbine corresponding to the slow-moving state is determined, and when a helicopter uses the slow-moving state, a rotor wing of the helicopter is generally in a minimum load state, so that the rotating speed of the power turbine is in a certain range, and if the interval between the rotating speed and the power turbine and the related critical rotating speed of the helicopter does not meet the requirement of safety margin and needs to be adjusted, in order to ensure the stable operation of the gas generator, the slow-moving rotating speed of the gas generator can only be increased, the fuel waste is caused, and the lower washing airflow when the helicopter stays on the ground is enhanced. On a helicopter, the slow-moving work time accounts for about 10% of the total work time of an engine, and fuel waste in a slow-moving state is not negligible. For a turboprop engine, if the interval between the critical speeds associated with the power turbine itself and the aircraft does not meet the requirement of a safety margin, the situation is similar to that of a turboshaft engine, and the rotating speed of the power turbine in a slow-running state can only be increased, so that the waste of fuel oil is caused.
In addition, the above design of continuous flow rate is not favorable for reducing the no-load output speed of the engine and for the propeller, rotor and lift fan which are discontinuously driven to change from the transmission of the engine to the transmission of the engine along with the change of the flight state for the turboshaft engine adopted by the compound high-speed helicopter, the shaft fan engine adopted by the rotor/wing conversion type high-speed helicopter and the turbofan engine which is adopted by the short-takeoff/vertical landing airplane and can drive the lift fan. Taking a lift fan of a short-distance takeoff/vertical landing aircraft as an example, the lift fan needs to be driven by an engine only during takeoff and landing, and does not need to be driven during cruising flight, therefore, an active control type friction clutch is generally arranged between the lift fan and a low-pressure turbine of a turbofan engine at present, when the lift fan needs to be switched from the engine transmission to the engine transmission, the requirement of stable work of a gas generator of the engine is considered, and in order to shorten the subsequent time for increasing the rotating speed again, the rotating speed of the gas generator can only be reduced to a certain degree, at the moment, the rotating speed of the low-pressure turbine of the engine is still higher, so that after the friction clutch is closed, the heating value is larger in the process of increasing the rotating speed of the lift fan to be consistent with the rotating speed of the low-pressure turbine, and the working reliability.
Therefore, it is a problem to be solved how to independently adjust the power turbine operating capacity while the gasifier operating conditions and the torque of the load are not changed.
Disclosure of Invention
The invention provides an adjustable engine of a power turbine, which aims to solve the technical problem that the working capacity of the power turbine cannot be independently adjusted when the working state of a gas generator is unchanged in the conventional gas turbine engine.
The technical scheme adopted by the invention is as follows:
a power turbine adjustable engine includes an air bleeding device disposed between a gas turbine and a power turbine for adjusting the operating capacity of the power turbine.
Further, the air bleeding device includes: the gas collecting ring cavity is arranged on the outer side of the outer wall of the runner between the turbines between the gas turbine and the power turbine, the gas collecting channel is arranged on the outer wall of the runner and enables gas to enter the gas collecting ring cavity from the runner between the turbines, and the gas collecting ring cavity is connected with a gas discharging pipeline used for outputting the gas.
Furthermore, the gas collecting channel is a plurality of gas collecting holes arranged on the circumferential direction of the outer wall of the flow channel or a gas collecting circumferential seam arranged on the outer wall of the flow channel.
Furthermore, a valve for opening and closing the air discharging device is arranged on the air discharging pipeline.
Further, an air bleed line communicates with the engine flowpath after the power turbine to join the bled off gas with the engine exhaust gas after the power turbine.
Further, the valve is an electrically or fluid actuated valve.
Further, the opening and closing of the air bleeding device is controlled by a control device of the engine.
Further, the control device of the engine controls the air bleeding device to be opened when the engine is in a slow running state or when the engine load is switched from not being driven by the engine to being driven by the engine, and controls the air bleeding device to be closed when the engine is normally operated.
Further, the engine is a turboshaft engine, a turboprop engine, a shaft fan engine for a rotor/wing conversion type high-speed helicopter or a turbofan engine for a drivable lift fan of a short take-off/vertical landing aircraft.
The invention has the following beneficial effects:
the invention relates to a power turbine adjustable engine, which is provided with an air bleeding device used for adjusting the working capacity of a power turbine between a gas turbine and the power turbine. When the working capacity of the power turbine needs to be reduced, the air bleeding device is opened, a part of gas is released, so that the gas entering the power turbine is reduced, the working capacity of the power turbine is reduced, when the load is constant and the state of the gas generator is unchanged, the rotating speed of the power turbine is reduced, on one hand, the requirement of the safety margin of the critical rotating speed of the power turbine is met, the waste of fuel oil caused by the fact that the requirement is met in a mode of increasing the slow vehicle rotating speed of the gas generator is avoided, on the other hand, when the load of the engine is switched from being not transmitted by the engine to being transmitted by the engine, the heating of the clutch is reduced in the process of increasing the load rotating speed.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the accompanying drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
fig. 1 is a schematic structural view of a power turbine adjustable engine according to a preferred embodiment of the present invention.
The reference numbers illustrate:
1. a gas turbine; 2. an outer wall of the flow passage; 3. a valve; 4. an air bleed line;
5. a power turbine; 6. a gas collecting ring cavity; 7. and a gas collecting hole.
Detailed Description
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
Referring to fig. 1, a preferred embodiment of the present invention provides a power turbine adjustable engine, including: an air bleeding device provided between the gas turbine 1 and the power turbine 5 for adjusting the operation capacity of the power turbine 5 releases a part of the combustion gas by the air bleeding device, thereby reducing the combustion gas entering the power turbine 5 and reducing the operation capacity of the power turbine 5.
Specifically, when the working capacity of the power turbine 5 needs to be reduced, the air bleeding device is opened to release a part of the combustion gas, so that the combustion gas entering the power turbine 5 is reduced, the working capacity of the power turbine 5 is reduced, and when the load is constant and the state of the gas generator is not changed, the rotating speed of the power turbine 5 is reduced, so that on one hand, the safety margin requirement of the critical rotating speed of the power turbine 5 is met, the waste of fuel oil caused by meeting the requirement in a mode of increasing the slow-speed rotating speed of the gas generator is avoided, and on the other hand, when the engine load is switched from non-engine transmission to engine transmission, the heating of the clutch is reduced in the process of increasing the load rotating speed, and the working performance and the service life.
Preferably, the air bleeding device comprises: the gas collecting ring cavity 6 arranged on the outer side of the outer wall 2 of the flow channel between the gas turbine 1 and the power turbine 5 and the gas collecting channel which is arranged on the outer wall 2 of the flow channel and enables the gas collecting ring cavity 6 to be communicated with the flow channel between the turbines are connected with a gas discharging pipeline 4 used for outputting gas on the gas collecting ring cavity 6.
In this embodiment, the gas collecting channel is a plurality of gas collecting holes 7 arranged in the circumferential direction of the flow channel outer wall 2, and in other embodiments, the gas collecting channel is a gas collecting circumferential seam arranged in the circumferential direction of the flow channel outer wall 2, so that the flow channel and the gas collecting circumferential cavity 6 between the turbines are uniformly communicated, the gas discharging effect is better, and the rotating speed of the power turbine 5 can be rapidly reduced.
In the embodiment, the gas collecting ring cavity 6 and the outer wall 2 of the flow channel are integrally formed; in other embodiments, the gas collecting ring cavity 6 is fixed on the outer wall 2 of the flow channel through a limiting device.
Preferably, the air release line 4 is provided with a valve 3 for controlling the release of air, controlling the opening and closing of the air release means. The valve 3 can be designed to be adjustable in opening degree as required for controlling the discharge amount of discharged gas.
Optionally, the valve 3 is an electrically or fluid actuated valve.
Optionally, the bleed line 4 communicates with the engine flowpath at the rear 5 of the power turbine. In the present embodiment, the bleed line 4 communicates with the engine flow path after the power turbine 5 to join the bypass gas with the engine exhaust gas after the turbine, but in other embodiments, the bleed line 4 may not communicate with the engine flow path after the power turbine 5.
Preferably, the control device of the engine controls the opening and closing of the air bleeding device, the air bleeding device is closed at ordinary times, when the air bleeding device needs to be opened, the opening instruction can be sent out together with an instruction of starting the engine to slow down or an instruction of switching the load device from non-transmission to transmission, and can also be sent out according to the judgment of the engine speed signal, such as: when the engine is judged to be in a slow running state through the rotating speed signal, the air discharging device is controlled to be opened, and when the engine is judged to be in a normal working state through the rotating speed signal, the air discharging device is controlled to be closed.
Preferably, the engine of the present invention includes, but is not limited to: turboshaft engines, turboprop engines, shaft-fan engines for rotor/wing conversion high-speed helicopters, turbofan engines for drivable lift fans of short-takeoff/vertical landing aircraft.
From the above description, it can be seen that the power turbine adjustable engine of the present invention comprises: an air bleed device disposed between the gas turbine and the power turbine for adjusting the operating capacity of the power turbine. When the working capacity of the power turbine needs to be reduced, the air bleeding device is opened, a part of the gas bypass is released, so that the gas entering the power turbine is reduced, the working capacity of the power turbine is reduced, when the load is constant and the state of the gas generator is unchanged, the rotating speed of the power turbine is reduced, on one hand, the safety margin requirement of the critical rotating speed of the power turbine is met, the waste of fuel oil caused by the fact that the requirement is met in a mode of increasing the slow rotating speed of the gas generator is avoided, on the other hand, when the engine load is switched from the non-engine transmission to the engine transmission, in the process of increasing the load rotating speed, the heat generation of the clutch is reduced, and the working performance and the service.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (3)
1. A power turbine adjustable engine, the engine type includes turboshaft engine, turbine propeller engine, shaft fan engine used for rotor/wing conversion type high-speed helicopter or turbofan engine used for short take-off/vertical landing aircraft and can drive lift fan, the flow between the power turbine and the turbine in front of the power turbine is designed continuously, the working capacity of the power turbine is determined by the working state of the gas generator, the working capacity of the power turbine is adjusted independently when the working state of the gas generator is unchanged, characterized in that,
the engine comprises air bleeding means arranged between the gas turbine (1) and the power turbine (5) for adjusting the operating capacity of the power turbine (5);
the air bleeding device is positioned in front of the power turbine (5) and is used for opening when the power turbine (5) needs to reduce the working capacity so as to reduce the gas entering the power turbine (5) and reduce the rotating speed of the power turbine (5);
the air bleeder comprises: a gas collecting ring cavity (6) arranged on the outer side of the runner outer wall (2) between the gas turbine (1) and the power turbine (5) and a gas collecting channel which is arranged on the runner outer wall (2) and enables the gas collecting ring cavity (6) to be communicated with the runner between the turbines, wherein a gas discharging pipeline (4) used for outputting gas is connected to the gas collecting ring cavity (6); the gas collecting channel is a plurality of gas collecting holes (7) arranged on the circumferential direction of the outer wall (2) of the runner, or the gas collecting channel is a gas collecting annular seam arranged on the circumferential direction of the outer wall (2) of the runner so as to uniformly communicate the runner between the turbines and the gas collecting annular cavity (6), so that the gas discharging effect is better, and the rotating speed of the power turbine (5) can be rapidly reduced;
the gas discharge pipeline (4) is provided with a valve (3) for controlling gas discharge, the opening and the closing of the gas discharge device are controlled, and the valve (3) is designed to be adjustable in opening degree and used for controlling the discharge amount of discharged gas;
the control device of the engine controls the opening and closing of the air bleeding device, and the air bleeding device is closed at ordinary times; when the engine needs to be started, the starting command is jointly sent out with a command of starting the engine to slow down or a command of switching the non-transmission to the transmission of a load device; or the opening instruction is sent out according to the judgment of the rotating speed signal of the engine, when the rotating speed signal is used for judging that the engine is in a slow vehicle state, the air discharging device is controlled to be opened, and when the rotating speed signal is used for judging that the engine is in a normal working state, the air discharging device is controlled to be closed by the control device; fuel waste caused by the fact that the safety margin requirement of the critical rotating speed of the power turbine (5) is met by increasing the slow-vehicle rotating speed of the fuel generator in the slow-vehicle state is avoided; and reducing clutch heating during increasing load speed when the engine load is switched from not being driven by the engine to being driven by the engine.
2. The power-turbine adjustable engine according to claim 1,
and the gas discharge pipeline (4) is communicated with an engine flow passage behind the power turbine (5) so as to enable the discharged gas to be converged with engine exhaust behind the power turbine (5).
3. The power-turbine adjustable engine according to claim 1,
the valve (3) is an electrically or fluid actuated valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710318415.7A CN107091162B (en) | 2017-05-08 | 2017-05-08 | Power turbine adjustable engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710318415.7A CN107091162B (en) | 2017-05-08 | 2017-05-08 | Power turbine adjustable engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107091162A CN107091162A (en) | 2017-08-25 |
| CN107091162B true CN107091162B (en) | 2019-12-20 |
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ID=59637763
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710318415.7A Active CN107091162B (en) | 2017-05-08 | 2017-05-08 | Power turbine adjustable engine |
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| Country | Link |
|---|---|
| CN (1) | CN107091162B (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2328460A1 (en) * | 1973-06-05 | 1975-01-02 | Motoren Turbinen Union | V/STOL. turbo-jet engine - has multi-flow and multi-drive shaft construction |
| US5280702A (en) * | 1991-02-25 | 1994-01-25 | Allied-Signal, Inc. | Method for rapidly changing the power output of a turbine engine |
| US5485717A (en) * | 1994-06-29 | 1996-01-23 | Williams International Corporation | Multi-spool by-pass turbofan engine |
| CN1639451A (en) * | 2002-03-05 | 2005-07-13 | 威廉斯国际有限公司 | Multi-spool by-pass turbofan engine |
| EP1617053A3 (en) * | 2004-07-16 | 2008-01-23 | Honeywell International Inc. | Gas turbine engine bleed air power assist system and method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102008024022A1 (en) * | 2008-05-16 | 2009-11-19 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine engine, in particular aircraft engine |
-
2017
- 2017-05-08 CN CN201710318415.7A patent/CN107091162B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2328460A1 (en) * | 1973-06-05 | 1975-01-02 | Motoren Turbinen Union | V/STOL. turbo-jet engine - has multi-flow and multi-drive shaft construction |
| US5280702A (en) * | 1991-02-25 | 1994-01-25 | Allied-Signal, Inc. | Method for rapidly changing the power output of a turbine engine |
| US5485717A (en) * | 1994-06-29 | 1996-01-23 | Williams International Corporation | Multi-spool by-pass turbofan engine |
| CN1639451A (en) * | 2002-03-05 | 2005-07-13 | 威廉斯国际有限公司 | Multi-spool by-pass turbofan engine |
| EP1617053A3 (en) * | 2004-07-16 | 2008-01-23 | Honeywell International Inc. | Gas turbine engine bleed air power assist system and method |
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| Publication number | Publication date |
|---|---|
| CN107091162A (en) | 2017-08-25 |
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