# Applications of the First Law to Heat Engines

1. ## Thermodynamic cycles and heat engines(VW, S & B: Chapter 9)

2. This section of the course is devoted to describing the basic fundamentals of how various heat engines work (e.g. a refrigerator, an IC engine, a jet). You will also learn how to model these heat engines as thermodynamic cycles and how to apply the First Law of Thermodynamics to estimate thermal efficiency and work output as a function of pressures and temperatures at various points in the cycle. This is called ideal cycle analysis. The estimates you obtain from the analysis represent the best achievable performance that may be obtained from a heat engine. In reality, the performance of these systems will be somewhat less than the estimates obtained from ideal cycle analysis–you will learn how to make more realistic estimates in 16.050.

We will deal with only "air-standard" thermodynamic cycles, where we ignore the changes in properties of the working fluid brought about by the addition of fuel or the presence of combustion products (we do of course account for the heat release that occurs due to the combustion of the fuel-air mixture). In general this is a good assumption since in typical combustion applications the fuel accounts for only about 5% of the mass of the working fluid.

Q5.3 (PDF)

### The Otto Cycle (VW, S & B: 9.13)

The Otto cycle is an idealization of a set of processes used by spark ignition internal combustion engines (2-stroke or 4-stroke cycles). These engines a) ingest a mixture of fuel and air, b) compress it, c) cause it to react, thus effectively adding heat through converting chemical energy into thermal energy, d) expand the combustion products, and then e) eject the combustion products and replace them with a new charge of fuel and air. The various steps are illustrated on page 9 of these notes.

We model all of these happenings by a thermodynamic cycle consisting of a set of processes all acting on a fixed mass of air contained in a piston-cylinder arrangement. The exhaust and intake processes are replaced by constant-volume cooling.

1. Representation of the heat engine as a thermodynamic cycle.

2. (Ingest mixture of fuel and air)

1’ - 2 Compress mixture quasi-statically and adiabatically

2 - 3 Ignite and burn mixture at constant volume (heat is added)

3 - 4 Expand mixture quasi-statically and adiabatically

4 - 1’’ Cool mixture at constant volume

(then repeat)

work ~ Force* distance ~ fuel use ~ heat added ~ T3 - T2

efficiency ~ work out/fuel use   3. Method for estimating thermal efficiency and work output (application of the First Law of Thermodynamics).

4.

1. Net work done by system = work of expansion + work of compression (-)

2. Both expansion and compression are adiabatic so

Dw = (u3 - u4) - (u2 - u1)

Assuming an ideal gas with constant cv

Dw = cv[(T3 - T4) - (T2 - T1)]

3. While the above expression is accurate, it is not all that useful. We would like to put the expression in terms of the typical design parameters: the compression ratio (v1/v2 = v4/v3), and the heat added during combustion (qcomb. = cv(T3-T2)).

4. For a quasi-static, adiabatic process, so we can write the net work as we also know that so and finally, the desired result in terms of typical design parameters: 5. The thermal efficiency of the cycle is so (Note that we could also rewrite this as: showing that the efficiency of an Otto cycle depends only on the temperature ratio of the compression process.) Q5.4 (PDF)

Homework 6 (PDF)

### Brayton Cycle (VW, S & B: 9.8-9.9, 9.12)

The Brayton cycle is an idealization of a set of thermodynamic processes used in gas turbine engines, whether for jet propulsion or for generation of electrical power.

1. Components of a gas turbine engine

2.  Schematics of typical military gas turbine engine: J57 turbojet with afterburning..

3. The thermodynamic cycle

4. The cycle consists of four processes: a) quasi-static adiabatic compression in the inlet and compressor, b) constant pressure heat addition in the combustor, c) quasi-static adiabatic expansion in the turbine and exhaust nozzle, and finally d) constant pressure cooling to get the working fluid back to the initial condition.

1 - 2 Adiabatic, quasi-static compression in inlet and

compressor

2 - 3 Combust fuel at constant pressure (i.e. add heat)

3 - 4 Adiabatic, quasi-static expansion in turbine

a. take work out and use it to drive the compressor

b. take remaining work out and use it to accelerate fluid for jet

propulsion, or to turn a generator for electrical power generation.

4 - 1 Cool the air at constant pressure

Then repeat 5. Estimating the performance of the engine

6. Our objective with the Brayton cycle is the same as for the Otto cycle. First to derive expressions for the net work and the thermal efficiency of the cycle, and then to manipulate these expressions to put them in terms of typical design parameters so that they will be more useful.

First, remember from the First Law we can show that for any cyclic process heat and work transfers are numerically equal

Du = q - w

ufinal = uinitial therefore Du = 0 and q = w or This fact is often useful for solving thermodynamic cycles. For instance in this example, we would like to find the net work of the cycle and we could calculate this by taking the difference of the work done all the way around the cycle. Or, since Dq = Dw, we could just as well consider the difference between the heat added to the cycle in process 2-3, and the heat rejected by the cycle in process 4-1.

1. heat added between 2-3 (combustor):

2. First Law in terms of enthalpy for an ideal gas undergoing a quasi-static process:

dq = dh - vdp or dq = cpdT - vdp

at constant pressure

3. heat rejected between 4-1:

4. similarly

qadded = cp DT or qrejected = cp (T4 - T1)

5. work done and thermal efficiency:

6. Dw = Dq = qadded - qrejected = cp[(T3 - T2) - (T4 - T1)]

hBrayton = (qadded - qrejected)/ qadded = [(T3 - T2) - (T4 - T1)]/(T3 - T2)

Again, while these expressions are accurate, they are not all that useful. We need to manipulate them to put them in terms of typical design parameters for gas turbine engines. For gas turbine engines the most useful design parameters to use for these equations are often the inlet temperature (T1), the compressor pressure ratio (p2/p1), and the maximum cycle temperature, the turbine inlet temperature (T3).

7. Rewriting equations in terms of design parameters:

8.  so with becomes and for the efficiency but from above so 9. Performance plots In the plot above, TR = T3/T1. Note that for a given turbine inlet temperature, T3, (which is set by material limits) there is a compressor pressure ratio that maximizes the work. Q5.5 (PDF)

Q5.7 (PDF)

### Generalized Representation of Thermodynamic Cycles (VW, S & B: 6.1) Note that heat engines can be represented generally as:

a transfer of heat from a high temperature reservoir to a device +

a rejection of heat from a device to a low temperature reservoir

+

net work done on surroundings

1. ### To obtain data for an operating gas turbine engine (the one that provides power to MIT!) checkout the following links:

http://cogen.mit.edu/

Homework 7 (PDF)

### E. Refrigeration Cycles

Refrigeration cycles take in work from the surroundings and transfer heat from a low temperature reservior to a high temperature reservior. Schematically, they look like the diagram given above, but with the direction of the arrows reversed. They can also be recognized on thermodynamic diagrams as closed loops with a counter-clockwise direction of travel. A more detailed physical description is given below. The objective of a refrigerator is to lower the internal energy of a body at low temperature (the food) and transfer that energy to the higher temperature surroundings (the room the refrigerator is in). It requires work (typically in the form of electrical energy) to do this. The medium for the energy exchange is a working fluid (a refrigerant) that circulates in a loop through a series of devices. These devices act to add and remove energy from the working fluid. Typically the working fluid in the loop is considered the thermodynamic system. Sometimes the fluid used alternates between gas-phase and liquid-phase, but this detail is not important for understanding the basic process. A sim plified schematic is shon above.

As the refrigerant circulates around the loop, its internal energy (and temperature) is alternately raised and lowered by a series of devices. In this manner, the working fluid so that it is colder than the refrigerator air at one point and hotter than the air in the room at another point. Thus heat will flow in the appropriate direction as shown by the two arrows in the heat exchangers. Starting in the upper right hand corner of the diagram, first the internal energy is lowered either by passing through a small turbine or through an expansion valve. In these devices, work is done by the refrigerant so its internal energy is lowered. The internal energy is lowered to a point where the temperature of the refrigerant is lower than that of the air in the refrigerator. A heat exchanger is used to transfer energy from the air (and food) in the refrigerator to the cold refrigerant (energy transferred by virtue of a temperature difference only = heat). This lowers the internal energy of the air/food and raises the internal energy of the refrigerant. Then a pump or compressor is used to do work on the refrigerant adding additional energy to it and thus further raising its internal energy. Electrical energy is used to drive the pump or compressor. The internal energy of the refrigerant is raised to a point where its temperature is hotter than the temperature of the room. The refrigerant is then passed through a heat exchanger (the coils at the back of the refrigerator) so that energy is transferred from the refrigerant to the surroundings. As a result, the internal energy of the refrigerant is reduced and the internal energy of the surroundings is increased. It is at this point where the internal energy of the food and the energy used to drive the compressor or pump are transferred to the surroundings. The refrigerant then continues on to the turbine, repeating the cycle.