Übersetzung für "Compressor load" in Deutsch

An optimized surge limit distance makes higher compressor pressures possible and therefore a higher compressor load.

The compressor load is typically greater than the turbine load on the high-pressure shaft of an aircraft gas turbine.

An optimized surge limit interval permits higher compressor pressures and thus a higher compressor load.

An optimized pump limit interval permits higher compressor pressures and thus a higher compressor load.

It is another object of the invention to indicate a method that permits condensate to be discharged from a multistage compressor at load operation and when said compressor is switched to an off condition, said method being suited to be developed in an simple manner so that drainage is also possible in such operating conditions of the compressor in which the reservoir is subjected to a negative pressure.

In order to avoid complete shutdown of the compressor, the instantaneous load torque is represented as a function of variables, such as compressor speed and high pressure of the refrigerant, and, using an inverted function belonging to this function, a control signal for the compressor, for example, a set-point value for the high pressure of the refrigerant, is determined as a function of the maximum limiting torque and employed to control the compressor.

To name an exemplary extreme case, it is also possible that in case that an extraordinary large need for pressurized air is indicated both air dryer cartridges are not regenerated but both air dryer cartridges are temporarily supplied with pressurized air from the compressor in a load phase of both air dryer cartridges.

It is also possible that for the control of the compressor, of the load phase and/or of a regeneration phase a detected or anticipated downhill drive is considered where a supply of pressurized air with increased pressure might be done without undesired energy losses.

This solution likewise has the advantage that, with it, it is possible to operate the operation of the turbo compressor in partial load operation with gas volume flows which are significantly reduced in comparison with the design point.

Positive effects for the operational stability of the turbo compressor under partial load and full load with an overall positive change in the efficiency, particularly under full load, can be linked hereby.

Therefore a common prime mover can be provided for driving these compressor stages, because the compressor load is distributed substantially uniformly among the aforementioned compressor stages.

For steady-state operation, the angular acceleration is equal to zero and therefore the following applies: Q=P geno /n (4), wherein the efficiency n for different operating states is known and can be determined as a function of the most important operating parameters, such as load, compressor inlet temperature, position of the compressor guide vanes, inlet pressure, etc., or can be stored in tables.

If the expansion machine can also be operated additionally as a compressor, a general load control process is obtained which enables a large load range of the internal combustion engine 1 with outstanding partial load fuel consumption.

Such unloaders essentially serve to start the compressor under no load or to switch the compressor to an idling operation.

The inventive idea starts from the concept that a compressor load is generated in flight direction (forward direction) and a turbine load is generated in opposite direction to the flight direction (backward direction) and involves applying reduced pressure of the compressor air to the rear side of the compressor of the high-pressure shaft and increased pressure of compressor air to the turbine or turbine disc to reduce the resulting load that acts on the locating bearing of the high-pressure shaft so that bearings can be used that enable high speeds and yet have a long service life.

The forward axial force from the compressor 1 and thus the difference between compressor load and turbine load that acts on the locating bearing is reduced by reducing the pressure generally across the entire length of the drive cone 11, i. e. by the formation of a low-pressure chamber 8 in this area, separated by brush-type seals 5 and 6 .

The compressor load can be decreased, and the turbine load increased, in a defined way, thereby optimally reducing the resulting load on the locating bearing of the high-pressure shaft, by the controlled setting of a specific low or high pressure in the low or high-pressure chambers 8, 9, respectively.

In a gas turbine, the compressor load is reduced and the turbine load is increased for controlled bearing load reduction by forming a low-pressure chamber (8) that is shielded from the compressor air at the compressor (1) and a high-pressure chamber (9) that is supplied with compressor air at the turbine along the high-pressure shaft (2).

As it is well known, unloaders serve substantially to start up the compressor under no load, or to switch the compressor to an idling operation, or to control the compressor.

Due to a frequency inverter the compressor never switches load/unload, as the number of rotations adapts itself to the energy consumption.

Run-time control for the compressors and load management result in continuous energy improvement.

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Relief of the pressure space can be effectively implemented by this check valve when the compressor is being loaded.

Due to the non-linearity of the compressors' characteristics, it will not for example always be immediately evident whether it is more effective to operate a smaller number of compressors at a full load or overloaded or a larger number of compressors at partial load.

The core of this method is to match the compressors with load distributors such that the operating points of all the compressors will always be the same distance away from their blowoff line.

The invention relates to an arrangement for influencing the radial clearance of the blading in axial-flow, highly loaded compressors of gas turbines.

According to the invention, in an axial-flow, highly loaded compressor which essentially comprises a rotor equipped with moving blades and a blade carrier which is equipped with guide blades and is hung in a casing, this is achieved when the blade carrier has long and narrow mountings for the guide blades, at least one hollow space being arranged in the guide-blade roots, and when a hollow space is present in each case in the embedded state in the peripheral direction between the guide-blade root, the two mountings for a guide blade and the blade carrier, and when a further hollow space is present in each case in the peripheral direction between the blade carrier and the mountings for two successive guide blades, which hollow space is defined by a plurality of segments distributed over the periphery and connected to the guide-blade roots, and when the hollow spaces are filled with insulating material.

In contrast to the flow principle of the turbo compressors, in partial load operation the displacement principle makes the rotary lobe compressor accordingly more efficient due to its high regulating range of 25 to 100% in low volume flow requirement.

In this context the compressor must perform considerable work counter to a high pressure prevailing in the compressed-air supply device 10, as a result of which the compressor is heavily loaded and experiences a risk of overheating.

With the aid of this device, a so-called cold air turbine operation of the compressor may be implemented in which a vacuum prevails in the induction system downstream of the compressor at low loads and speeds of the internal combustion engine, which vacuum causes a pressure drop across the compressor wheel that can be utilized to drive the compressor wheel.

During operation of the stator vane spans in a compressor, high mechanical loads and temperature changes are encountered which can affect the fits used for attachment.