Question
In: Statistics and Probability
A study was conducted on a high-pressure inlet fogging method for a gas turbine engine. Researchers...
A study was conducted on a high-pressure inlet fogging method for a gas turbine engine. Researchers considered two models. Partial output is provided below.
|
Source |
Df |
SS |
MS |
F |
|
Regression |
5 |
148526859 |
29705372 |
94 |
|
Error |
61 |
19370350 |
317547 |
|
|
Total |
??? |
167897208 |
|
Source |
Df |
SS |
MS |
F |
|
Regression |
??? |
142586570 |
47528857 |
??? |
|
Error |
63 |
25310639 |
401756 |
|
|
Total |
??? |
167897208 |
Answer the following questions rounding off at the nearest integer.
1. The number of observations collected for the study is equal to
2. The number of predictors considered in the reduced model is equal to
3. The F-test for global utility of the reduced model is equal to
Results suggest that the complete model provides additional information compared to the reduced model. In fact, the F-test for nested models is equal to 4.
which is greater than the rejection region F(alpha =0.05) with numerator degrees of freedom equal to 5.
and denominator degrees of freedom equal to 6.
Solutions
orchestra answered 1 year agoRelated Solutions
A study was conducted on a high-pressure inlet fogging method for a gas turbine engine. Researchers...
A study was conducted on a high-pressure inlet fogging method
for a gas turbine engine. Researchers considered two models.
Partial output is provided below.
Source
Df
SS
MS
F
Regression
5
148526859
29705372
94
Error
61
19370350
317547
Total
???
167897208
Source
Df
SS
MS
F
Regression
???
142586570
47528857
???
Error
63
25310639
401756
Total
???
167897208
Answer the following questions rounding off at the nearest
integer.
The number of observations collected for the study is equal
to
The...
Cooling method for gas turbines. Refer to the Journal of Engineering for Gas Turbines and Power (January 2005) study of a high-pressure inlet fogging method for a gas turbine engine
Cooling method for gas turbines. Refer to the Journal of Engineering for Gas Turbines and Power (January 2005) study of a high-pressure inlet fogging method for a gas turbine engine, Exercise 4.13 (p. 188). Recall that you fit a first order model for heat rate (y) as a function of speed (x1), inlet temperature (x2), exhaust temperature (x3), cycle pressure ratio (x4), and air flowrate(x5) to data saved in the GASTURBINE file.
(a) Researchers hypothesize that the linear relationship between...
The temperature and pressure of the steam at the inlet of a high pressure turbine is...
The temperature and pressure of the steam at the inlet of a high pressure turbine is 500 ° C, respectively. It is 12 MPa and 300 ° C and 3MPa at its outlet. If the mass flow of steam is 400 kg / h, how much is the isentropic efficiency of the turbine?
In a marine gas turbine unit a high-pressure turbine drives the compressor, and a low-pressure turbine...
In a marine gas turbine unit a high-pressure turbine drives the
compressor, and a low-pressure turbine drives the propeller through
suitable gearing. The overall pressure ratio is 4/1, and the
maximum temperature is 650⁰C. The isentropic efficiencies of the
compressor, High Pressure turbine, and Low Pressure turbine are
0.8, 0.83 and 0.85 respectively, and the mechanical efficiency of
both shafts is 98%.
Calculate the pressure entering the Low Pressure turbine when
the air intake conditions are 1.01 bar and 25⁰C....
An ideal Rankine cycle operates with a turbine inlet pressure of 600 psia and a turbine...
An ideal Rankine cycle operates with a turbine inlet pressure of
600 psia and a turbine inlet temperature of 526 oF. The steam is
isentropically expanded through the turbine to 15 psia as
illustrated on the T-s diagram shown below. Using the Mollier
diagram, determine the enthalpy at the turbine inlet, in BTU/lbm,
under these operating conditions. State your answer in whole
numbers.
An ideal Rankine cycle operates with a turbine inlet pressure of 900 psia and a turbine...
An ideal Rankine cycle operates with a turbine inlet pressure of
900 psia and a turbine inlet temperature of 572 oF. The steam is
isentropically expanded through the turbine to 5 psia as
illustrated on the T-s diagram shown below. Using the Mollier
diagram, determine the percent moisture at the turbine outlet under
these operating conditions. State your answer in whole numbers.
A gas turbine engine is considered in a race car design. The engine operates on two...
A gas turbine engine is considered in a race car design. The
engine operates on two stages of compression with intercooling and
two stages of expansion. The pressure ratio across each stage of
the compressor and the turbine is 7. The air enters each stage of
the compressor at 300K and each stage of the turbine at 1300K.
Using air standard assumptions determine:
Thermal efficiency and back work ratio if no regenerator is
used;
Thermal efficiency and back work ratio...
Steam expands in a thermally isolated turbine steadily. The inlet pressure is 1MPa and temperature is...
Steam expands in a thermally isolated turbine steadily.
The inlet pressure is 1MPa and temperature is 800 C, and the
exit state is 300 kPA and 150 C.
a- Determine the power generated by the turbine per unit mass
flow rate of steam.
b- Evaluate the entropy generation rate per unit mass flow rate
of steam and drive a conclusion whether the turbine operates
reversibly, irreversibly or the operation is impossible.
Consider a gas turbine engine, fueled by natural gas, for generating electricity. A.) Calculate the adiabatic...
Consider a gas turbine engine, fueled by natural gas, for
generating electricity.
A.) Calculate the adiabatic flame temperature for this system,
assuming we’ll use about 110% TA.
B.) Estimate (calculate) the power output for this turbine, per
lbm or kg of air.
C.) If I’d like to provide the generator with 12,000 shp (shaft
horsepower), what air mass flow do I need?
D.) If this is an open cycle turbine, the exhaust gas has
considerable remaining energy. How much heat...
a) An open cycle gas turbine engine consists of a compressor, a combustion chamber and a...
a) An open cycle gas turbine engine consists of a compressor, a
combustion chamber and a two-stage turbine with a re-heater. The
gas enters the compressor at a temperature of 15 C. The pressure
ratio of the compressor, which is 90% efficient, is 12. The
combustion gas enters the first stage turbine at 1100 C. Both
stages of the turbine are 95% efficient. The first stage has a
pressure ratio of 4, whereas that of the second stage is 3....
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