|
Problem
|
The purpose and constraints
|
Type of object
representation
|
Number of
variables/
constraints |
The class
of goal function
|
Number of solved problems
|
| Optimization of geometrical
parameters of the multistage axial compressor |
1. The magnification of efficiency on design
operational mode of gas-turbine engine or power installation at observance
of constraints on air consumption, compressor operation stability
and strength of details. |
Mathematical model
|
4 - 99/
8 - 220
|
Multiextreme, nondifferentiable
|
> 60
|
| 2. The magnification of compressor efficiency
on several operational modes of gas-turbine engine at observance of
constraints on air consumption, operation stability and strength of
details. (Multicriteria approach). |
Mathematical model
|
4 - 99/
8 - 600
|
Multiextreme, nondifferentiable
|
> 40
|
| 3. The maximization of efficiency ensured
with preset probability at a preset accuracy of details manufacturing
and preset probability of constraints insurance. |
Mathematical model
|
4 - 63/
12 - 280
|
Stochastic
|
> 30
|
| The joint optimization of geometrical parameters
and blades rows control laws of multistage axial compressor |
The maximization of efficiency for a specific
range of operational modes at observance of constraints on air consumption,
compressor operation stability and strength of details |
Mathematical model
|
4-63/
8 - 250
|
Multiextreme, nondifferentiable
|
12
|
| The optimization of work process parameters
of gas-turbine engine of versatile aircraft |
The choice of optimal values of design
and gas-dynamic parameters of gas-turbine engine for given totality
of aircraft flight modes |
Mathematical model
|
3/4
|
Nonconvex
|
2
|
| The searching of Pareto-optimal set of
multistage axial compressor parameters and control laws for a preset
set of engine operational modes. |
The minimization of fuel consumption for
each of specified operational modes at observance of restrictions
on operation stability and strength of details. (Multicriteria optimization). |
Mathematical model
|
6 - 18/6
|
Multiextreme
|
3
|
| The optimization of control law of the
serial gas-turbine engine controllable elements. |
Searching of positions of controllable
elements to be Pareto-optimal on "thrust" and "fuel
consumption" criteria at observance of constraints on components
stability margins and on gas temperature at turbine inlet. (Multicriteria
optimization). |
Mathematical model
|
3 - 4/5
|
Nonconvex
|
10
|
| The multipurpose optimization of STOVL
aircraft power plant design parameters and control laws. |
The magnification of vertical thrust and
low pressure compressor stability margins at observance of constraints
on other elements stability margins, temperatures of gas at turbine
inlet and nozzles outlets, on rotors rotation rates and on the thrust
modulation margin |
Mathematical model
|
8/6
|
Nonconvex
|
9
|
| The multipurpose optimization of time control
laws of power plant of STOVL aircraft for it’s short take-off |
The decreasing of take-off run length and
fuel consumption for STOVL aircraft short take-off from it’s
start to evolutive velocity and safe altitude reaching at observance
of constraints on stability margins, temperature of gas and rotors
rotation rates |
Mathematical model
|
Up to 53/8
|
Multiextreme
|
6
|
| The optimization of control
laws of aircraft gas-turbine engine at non-stationary perturbations
of inlet stream |
1. The preservation of steady engine operation
at minimum losses of thrust impulse for specified parameters of perturbation. |
Mathematical model
|
48-216/
26
|
Multiextreme
|
> 20
|
| 2. The maximization of probability of steady
operation and minimization of expectation of thrust impulse losses
for specified perturbation probability performances. |
Mathematical model
|
24-112/
26
|
Stochastic
|
13
|
| 3. Raise of probability of steady operation
at a lack of information about perturbation parameters. |
Mathematical model
|
16-48/5
|
Multiextreme
|
8
|
| The optimization of aircraft gas-turbine
engine controllable elements control laws at maneuvering of aircraft. |
The minimization of maneuver execution
time and fuel consumption at constraint on aircraft overload and admissible
angles of attack and on engine operation stability. |
Mathematical model
|
20 - 70/5
|
Multiextreme
|
> 20
|
| The optimization of parameters and control
programs of gas-turbine engines, which have completed resource, in
a structure of ground power installations |
The minimization of fuel consumption, the
minimization of thrust and maximization of outlet temperature for
gas-turbine engine in a structure of the thermal machine. (Multicriteria
approach) |
Mathematical model + actual plant
|
3 - 5/3
|
Multiextreme
|
3
|
| The optimal calibration of the microprocessor
control system of automobile engine. |
The minimization of fuel consumption at
specified constraints on exhaust toxicity |
Actual plant on the experimental bench
|
3/3
|
Stochastic
|
2
|
| The optimization of multilayer optical
coatings. |
Minimization of surface reflection (absorption)
coefficient in a specified range of lengths of waves |
Mathematical model
|
6 - 20/57
|
Multiextreme, ravine
|
6
|
