8.3 Thermal Radiation, Emissivity, and Surface Radiation Exchange

8.3 Thermal Radiation, Emissivity, and Surface Radiation Exchange

Thermal radiation is the transfer of energy across space by electromagnetic waves in the wavelength band between approximately $0.1,\mu\text{m}$ and $100,\mu\text{m}$ (encompassing parts of ultraviolet, the entire visible spectrum, and infrared). Unlike conduction and convection, thermal radiation requires no physical matter or intervening medium; it propagates most efficiently through a vacuum.

In chemical manufacturing, radiation is the dominant mode of heat transfer in steam-methane reformers, ethylene cracking furnaces, thermal oxidizers, and flare headers, where process temperatures exceed $700^\circ\text{C}$ ($1300^\circ\text{F}$). Radiation is also paramount in cryogenic liquid storage (liquid nitrogen, liquid oxygen, LNG), where multi-layer radiation shields prevent catastrophic product boil-off.

---

1. Physical Nature of Thermal Radiation & Blackbody Radiation

All matter at a non-zero absolute temperature continuously emits thermal radiation due to rotational, vibrational, and electronic transitions of its constituent atoms and molecules.

The Blackbody Concept

A blackbody is an idealized thermodynamic body that possesses two fundamental properties:

1. It absorbs all incident thermal radiation regardless of wavelength or direction (absorptivity $\alpha = 1.0$).
2. At a given temperature and wavelength, no real surface can emit more energy than a blackbody (emissivity $\epsilon = 1.0$).

Stefan-Boltzmann Law

Integrating Planck's spectral radiation distribution over all wavelengths ($0 \le \lambda \le \infty$) and over all hemispherical solid angles ($2\pi\text{ sr}$) yields the total emissive power of a blackbody:

$E_b(T) = \sigma T^4$

Where:

• $E_b$ = total blackbody emissive power ($\text{W/m}^2$ or $\text{Btu/(hr}\cdot\text{ft}^2)$).
• $T$ = absolute temperature ($\text{K}$ or $^\circ\text{R}$).
• $\sigma$ = Stefan-Boltzmann constant: $\sigma = 5.67037 \times 10^{-8}\text{ W/(m}^2\cdot\text{K}^4) = 0.1714 \times 10^{-8}\text{ Btu/(hr}\cdot\text{ft}^2\cdot^\circ\text{R}^4)$

Wien's Displacement Law

The wavelength $\lambda_{max}$ at which spectral emissive power peaks is inversely proportional to absolute temperature:

$\lambda_{max} T = 2,897.8\,\mu\text{m}\cdot\text{K} = 5,215.6\,\mu\text{m}\cdot^\circ\text{R}$

As a furnace heats up from $300\text{ K}$ to $1500\text{ K}$, $\lambda_{max}$ shifts from the far infrared ($9.66,\mu\text{m}$) into the visible spectrum ($1.93,\mu\text{m}$), causing refractory walls to glow cherry-red.

---

2. Surface Radiative Properties: Emissivity, Absorptivity, and Kirchhoff's Law

Real engineering materials emit and absorb less radiation than an ideal blackbody at the same temperature.

Radiative Balances on an Opaque Surface

When radiation flux $G$ (called irradiation, $\text{W/m}^2$) strikes a material surface, it is partitioned into absorbed, reflected, and transmitted portions:

$\alpha + \rho + \tau = 1$

Where $\alpha$ is absorptivity, $\rho$ is reflectivity, and $\tau$ is transmissivity. For most structural engineering materials (metals, bricks, refractory linings), the material is opaque to thermal radiation ($\tau = 0$):

$\alpha + \rho = 1 \implies \rho = 1 - \alpha$

Emissivity ($\epsilon$)

The total hemispherical emissivity is the ratio of the total emissive power $E$ of a real surface to that of a blackbody at the identical temperature:

$\epsilon(T) \equiv \frac{E(T)}{E_b(T)} = \frac{E(T)}{\sigma T^4} \quad (0 \le \epsilon \le 1)$

Kirchhoff's Law of Thermal Radiation

For a small body in thermodynamic equilibrium inside an isothermal black enclosure, the rate of emission must equal the rate of absorption. Kirchhoff demonstrated that at any given wavelength $\lambda$ and direction:

$\alpha_\lambda(T) = \epsilon_\lambda(T)$

A gray surface is defined as one whose monochromatic properties are independent of wavelength ($\epsilon_\lambda = \text{constant}$). A diffuse surface emits and reflects radiation uniformly in all directions. For a gray, diffuse surface in thermal equilibrium:

$\alpha = \epsilon$

---

3. Radiosity, Irradiation, and Surface Radiation Resistance

To analyze radiation exchange between real surfaces, chemical engineers use the network method developed by Hoyt C. Hottel and Ascher H. Shapiro.

Radiosity ($J$)

Radiosity ($J$, $\text{W/m}^2$) is the total radiative flux leaving a surface per unit area, combining both emitted radiation and reflected incoming irradiation:

$J = E + \rho G = \epsilon E_b + (1 - \alpha) G$

Applying Kirchhoff's law ($\alpha = \epsilon$):

$J = \epsilon E_b + (1 - \epsilon) G \implies G = \frac{J - \epsilon E_b}{1 - \epsilon}$

Surface Resistance to Radiation

The net rate of heat transfer leaving a surface of area $A$ is the difference between radiosity leaving and irradiation arriving:

$q = A (J - G) = A \left[ J - \frac{J - \epsilon E_b}{1 - \epsilon} \right] = \frac{E_b - J}{\frac{1 - \epsilon}{\epsilon A}}$

This equation resembles Ohm's law ($I = \Delta V / R$):

• Driving potential: $E_b - J$ (blackbody emissive power minus radiosity).
• Surface resistance to radiation: $R_{surf} = \frac{1 - \epsilon}{\epsilon A}$

If a surface is a blackbody ($\epsilon = 1.0$), its surface resistance is zero ($R_{surf} = 0$), and its radiosity equals its blackbody emissive power ($J = E_b$).

---

4. View Factors & Geometric Enclosure Relations

The view factor (also known as the configuration factor, shape factor, or angle factor) $F_{ij}$ is defined as the fraction of radiation leaving surface $i$ that directly intercepts surface $j$:

$F_{ij} \equiv \frac{q_{i \to j}}{A_i J_i}$

Essential View Factor Rules for the PE Exam

1. Reciprocity Rule: $A_i F_{ij} = A_j F_{ji}$ Critical application: If you know $F_{12}$ and the areas $A_1$ and $A_2$, you can immediately calculate $F_{21} = (A_1 / A_2) F_{12}$.

2. Summation Rule (Enclosure Rule): For an enclosure composed of $N$ discrete surfaces completely enclosing a volume: $\sum_{j=1}^N F_{ij} = 1 \quad \text{for any surface } i$

3. Self-View Factor ($F_{ii}$):

   • For a flat (planar) surface: $F_{ii} = 0$ (cannot intercept its own straight-line rays).
   • For a convex surface (e.g., exterior of a cylinder or sphere): $F_{ii} = 0$.
   • For a concave surface (e.g., inside of a hemispherical cup or cylinder bore): $F_{ii} > 0$.

4. Superposition Rule: If surface $j$ is subdivided into non-overlapping sub-surfaces $k$ and $m$: $F_{i(k+m)} = F_{ik} + F_{im}$

---

5. Radiation Exchange Between Gray Diffuse Surfaces

Space Resistance

The net rate of radiation exchange between surface $i$ and surface $j$ is governed by the difference in their radiosities and the geometric space resistance:

$q_{ij} = \frac{J_i - J_j}{\frac{1}{A_i F_{ij}}} = \frac{J_i - J_j}{R_{space}}$

Where the space resistance is:

$R_{space} = \frac{1}{A_i F_{ij}} = \frac{1}{A_j F_{ji}}$

Two-Surface Enclosure Network

For an enclosure consisting of two gray, diffuse surfaces ($A_1, \epsilon_1, T_1$) and ($A_2, \epsilon_2, T_2$), the total equivalent resistance between $E_{b1}$ and $E_{b2}$ is the series sum of two surface resistances and one space resistance:

$R_{net} = R_{surf,1} + R_{space} + R_{surf,2} = \frac{1 - \epsilon_1}{\epsilon_1 A_1} + \frac{1}{A_1 F_{12}} + \frac{1 - \epsilon_2}{\epsilon_2 A_2}$

$q_{12} = \frac{E_{b1} - E_{b2}}{R_{net}} = \frac{\sigma (T_1^4 - T_2^4)}{\frac{1 - \epsilon_1}{\epsilon_1 A_1} + \frac{1}{A_1 F_{12}} + \frac{1 - \epsilon_2}{\epsilon_2 A_2}}$

(E_b1) ---[ (1-eps1)/(eps1*A1) ]---> (J_1) ---[ 1/(A1*F12) ]---> (J_2) ---[ (1-eps2)/(eps2*A2) ]---> (E_b2)

Common Industrial Special Geometries

1. Large Infinite Parallel Plates

For two infinite parallel plates, $A_1 = A_2 = A$ and $F_{12} = 1$:

$\frac{q_{12}}{A} = \frac{\sigma (T_1^4 - T_2^4)}{\frac{1}{\epsilon_1} + \frac{1}{\epsilon_2} - 1}$

2. Long Concentric Cylinders or Concentric Spheres

Surface 1 (inner body) is enclosed completely by surface 2 (outer shell). Therefore, $F_{12} = 1$:

$q_{12} = \frac{\sigma A_1 (T_1^4 - T_2^4)}{\frac{1}{\epsilon_1} + \frac{1 - \epsilon_2}{\epsilon_2} \left( \frac{A_1}{A_2} \right)}$

3. Small Convex Object in a Large Enclosure

When a relatively small process pipe or thermocouple probe ($A_1$) is enclosed in a large room or furnace chamber ($A_2$), the area ratio $A_1 / A_2 \to 0$. Substituting $A_1 / A_2 = 0$ into the concentric formula:

$q_{12} = \epsilon_1 \sigma A_1 (T_1^4 - T_{surr}^4)$

[!NOTE] Notice that the emissivity of the large surrounding enclosure ($\epsilon_2$) drops completely out of the equation! A small object "sees" the large enclosure effectively as a blackbody cavity, regardless of $\epsilon_2$.

---

6. Radiation Shields and Multi-Layer Insulation

A radiation shield is a thin sheet of high-reflectivity, low-emissivity material (such as polished aluminum foil or gold-coated mylar) placed between two radiating surfaces to reduce radiative heat transfer without carrying structural loads.

Analysis of a Single Radiation Shield

Consider two large parallel plates ($1$ and $2$) with a thin radiation shield ($3$) of emissivity $\epsilon_3$ placed between them. The network now contains two space resistances and four surface resistances in series:

$R_{shielded} = \left( \frac{1 - \epsilon_1}{\epsilon_1 A} \right) + \frac{1}{A} + \left( \frac{1 - \epsilon_3}{\epsilon_3 A} \right) + \left( \frac{1 - \epsilon_3}{\epsilon_3 A} \right) + \frac{1}{A} + \left( \frac{1 - \epsilon_2}{\epsilon_2 A} \right)$

If all surfaces (plates and shield) have the same emissivity ($\epsilon_1 = \epsilon_2 = \epsilon_3 = \epsilon$):

$\left(\frac{q}{A}\right)_{1\text{ shield}} = \frac{1}{2} \left(\frac{q}{A}\right)_{unshielded}$

Generalization to $N$ Shields

For $N$ radiation shields of identical emissivity placed between two infinite parallel plates:

$\left(\frac{q}{A}\right)_{N\text{ shields}} = \frac{1}{N + 1} \left(\frac{q}{A}\right)_{unshielded}$

For example, inserting $N = 3$ shields reduces the radiative heat transfer to exactly $1/(3+1) = 25%$ of its unshielded value (a $75%$ reduction).

Equilibrium Temperature of a Single Shield

At steady state, the heat flux entering the shield equals the heat flux leaving it ($q_{13} = q_{32}$):

$T_3^4 = \frac{T_1^4 + T_2^4}{2} \implies T_3 = \left( \frac{T_1^4 + T_2^4}{2} \right)^{1/4}$

---

7. Combined Convection-Radiation & The Linearized Radiation Coefficient

In chemical plants, process equipment loses heat simultaneously by convection to the surrounding air at $T_\infty$ and by radiation to the surrounding structural walls at $T_{surr}$:

$q_{total} = q_{conv} + q_{rad} = h_c A (T_s - T_\infty) + \epsilon \sigma A (T_s^4 - T_{surr}^4)$

The Linearized Radiation Coefficient ($h_r$)

Factoring the fourth-power temperature difference:

$T_s^4 - T_{surr}^4 = (T_s^2 - T_{surr}^2)(T_s^2 + T_{surr}^2) = (T_s - T_{surr})(T_s + T_{surr})(T_s^2 + T_{surr}^2)$

We define the linearized radiation heat transfer coefficient $h_r$:

$h_r \equiv \epsilon \sigma (T_s + T_{surr})(T_s^2 + T_{surr}^2)$

So that:

$q_{rad} = h_r A (T_s - T_{surr})$

When the ambient fluid temperature equals the surrounding wall temperature ($T_\infty = T_{surr}$), convection and radiation act as two parallel heat transfer paths driven by the identical temperature difference $(T_s - T_\infty)$:

$q_{total} = (h_c + h_r) A (T_s - T_\infty) = h_{combined} A (T_s - T_\infty)$

Where the combined heat transfer coefficient is:

$h_{combined} = h_c + h_r$

---

8. Summary Table: Radiation Exchange Formulations Across Common Geometries

---

9. Comprehensive Worked Numerical Example: Ethylene Pyrolysis Transfer Line Radiation Loss and Shield Design

Problem Statement

An uninsulated high-alloy transfer line carrying effluent gas from an ethylene cracking furnace passes through an enclosed recovery bay. The transfer line has an outside diameter $D_1 = 0.200\text{ m}$ ($r_1 = 0.100\text{ m}$) and a length $L = 5.00\text{ m}$. The outer pipe surface operates at $T_1 = 800.0^\circ\text{C}$ ($1073.15\text{ K}$) with an oxidized stainless steel emissivity $\epsilon_1 = 0.80$.

The pipe is enclosed inside a large concrete furnace enclosure whose walls are maintained at $T_2 = 100.0^\circ\text{C}$ ($373.15\text{ K}$) with emissivity $\epsilon_2 = 0.90$. The stagnant air within the enclosure is at $T_\infty = 100.0^\circ\text{C}$ ($373.15\text{ K}$), with a natural convection heat transfer coefficient $h_c = 8.50\text{ W/(m}^2\cdot\text{K)}$.

Calculate:

1. The radiative heat loss rate ($q_{rad}$) and convective heat loss rate ($q_{conv}$) from the unshielded pipe, and the percentage contribution of radiation to total heat loss.
2. The linearized radiation heat transfer coefficient $h_r$ and the combined heat transfer coefficient $h_{combined}$.
3. To protect sensitive instrumentation, a thin cylindrical concentric radiation shield with diameter $D_s = 0.300\text{ m}$ and emissivity $\epsilon_s = 0.050$ (polished aluminum on both inner and outer surfaces) is installed around the pipe. Determine the steady-state equilibrium temperature of the shield ($T_s$) in Kelvin and Celsius.
4. Calculate the new radiative heat loss rate ($q_{rad,shielded}$) and the percentage reduction in radiation heat loss achieved by the shield.

---

Step 1: Unshielded Heat Loss (Convection and Radiation)

Outer pipe surface area: $A_1 = \pi D_1 L = \pi (0.200\text{ m})(5.00\text{ m}) = \mathbf{3.14159\text{ m}^2}$

Because the pipe is small relative to the large enclosure ($A_1 \ll A_2$, so $A_1 / A_2 \to 0$ and $F_{12} = 1$): $q_{rad} = \epsilon_1 \sigma A_1 (T_1^4 - T_2^4)$ $T_1^4 = (1073.15\text{ K})^4 = 1.32631 \times 10^{12}\text{ K}^4$ $T_2^4 = (373.15\text{ K})^4 = 1.9388 \times 10^{10}\text{ K}^4 = 0.01939 \times 10^{12}\text{ K}^4$ $T_1^4 - T_2^4 = 1.32631 \times 10^{12} - 0.01939 \times 10^{12} = 1.30692 \times 10^{12}\text{ K}^4$

$q_{rad} = (0.80) \times (5.67037 \times 10^{-8}\text{ W/(m}^2\cdot\text{K}^4)) \times (3.14159\text{ m}^2) \times (1.30692 \times 10^{12}\text{ K}^4)$ $q_{rad} = \mathbf{186,303\text{ W}} = \mathbf{186.30\text{ kW}}$

Convective heat loss: $q_{conv} = h_c A_1 (T_1 - T_\infty) = (8.50\text{ W/(m}^2\cdot\text{K)})(3.14159\text{ m}^2)(800.0 - 100.0\text{ K})$ $q_{conv} = (8.50)(3.14159)(700.0) = \mathbf{18,692\text{ W}} = \mathbf{18.69\text{ kW}}$

Total unshielded heat loss: $q_{total} = q_{rad} + q_{conv} = 186.30 + 18.69 = \mathbf{204.99\text{ kW}}$

$\text{Radiation Fraction} = \frac{186.30\text{ kW}}{204.99\text{ kW}} \times 100\% = \mathbf{90.88\%}$

Radiation constitutes over $90%$ of the total heat dissipation at this elevated operating temperature.

---

Step 2: Linearized Radiation Coefficient

$h_r = \frac{q_{rad}}{A_1 (T_1 - T_2)} = \frac{186,303\text{ W}}{(3.14159\text{ m}^2)(700.0\text{ K})} = \mathbf{84.72\text{ W/(m}^2\cdot\text{K)}}$

Combined heat transfer coefficient: $h_{combined} = h_c + h_r = 8.50 + 84.72 = \mathbf{93.22\text{ W/(m}^2\cdot\text{K)}}$

---

Step 3: Equilibrium Temperature of the Cylindrical Radiation Shield

Shield surface area: $A_s = \pi D_s L = \pi (0.300\text{ m})(5.00\text{ m}) = \mathbf{4.71239\text{ m}^2}$ $\frac{A_1}{A_s} = \frac{D_1}{D_s} = \frac{0.200}{0.300} = \frac{2}{3} = 0.66667$

Radiative exchange from pipe (1) to concentric shield (s): $q_{1s} = \frac{\sigma A_1 (T_1^4 - T_s^4)}{\frac{1}{\epsilon_1} + \frac{1 - \epsilon_s}{\epsilon_s}\left(\frac{A_1}{A_s}\right)}$ Denominator: $\frac{1}{0.80} + \frac{1 - 0.050}{0.050}(0.66667) = 1.250 + (19.00)(0.66667) = 1.250 + 12.667 = 13.917$ $q_{1s} = \frac{\sigma A_1 (T_1^4 - T_s^4)}{13.917}$

Radiative exchange from shield (s) to the large enclosure (2) ($A_s \ll A_2$, so $A_s / A_2 \to 0$): $q_{s2} = \epsilon_s \sigma A_s (T_s^4 - T_2^4) = (0.050) \sigma A_s (T_s^4 - T_2^4)$

Equating $q_{1s} = q_{s2}$ at steady state: $\frac{\sigma A_1 (T_1^4 - T_s^4)}{13.917} = 0.050 \sigma A_s (T_s^4 - T_2^4)$ $\frac{A_1 / A_s}{13.917} (T_1^4 - T_s^4) = 0.050 (T_s^4 - T_2^4)$ $\frac{0.66667}{13.917} (T_1^4 - T_s^4) = 0.047903 (T_1^4 - T_s^4) = 0.050 (T_s^4 - T_2^4)$

Rearranging for $T_s^4$: $0.047903 T_1^4 - 0.047903 T_s^4 = 0.050 T_s^4 - 0.050 T_2^4$ $(0.047903 + 0.050) T_s^4 = 0.047903 T_1^4 + 0.050 T_2^4$ $0.097903 T_s^4 = 0.047903 (1.32631 \times 10^{12}) + 0.050 (1.9388 \times 10^{10})$ $0.097903 T_s^4 = 6.35345 \times 10^{10} + 0.09694 \times 10^{10} = 6.45039 \times 10^{10}$ $T_s^4 = \frac{6.45039 \times 10^{10}}{0.097903} = 6.58855 \times 10^{11}\text{ K}^4$ $T_s = (6.58855 \times 10^{11})^{0.25} = \mathbf{900.5\text{ K}} = \mathbf{627.35^\circ\text{C}}$

---

Step 4: Shielded Radiative Heat Loss & Reduction

Calculate $q_{rad,shielded}$ using $q_{s2}$: $q_{rad,shielded} = 0.050 \sigma A_s (T_s^4 - T_2^4)$ $q_{rad,shielded} = (0.050)(5.67037 \times 10^{-8}\text{ W/(m}^2\cdot\text{K}^4))(4.71239\text{ m}^2)(6.58855 \times 10^{11} - 1.9388 \times 10^{10}\text{ K}^4)$ $q_{rad,shielded} = (1.33606 \times 10^{-8})(6.39467 \times 10^{11}) = \mathbf{8,544\text{ W}} = \mathbf{8.54\text{ kW}}$

$\text{Heat Loss Reduction} = \frac{q_{rad,unshielded} - q_{rad,shielded}}{q_{rad,unshielded}} \times 100\% = \frac{186.30 - 8.54}{186.30} \times 100\% = \mathbf{95.42\%}$

A single polished aluminum shield reduces radiant heat loss by over $95%$, drastically lowering the thermal burden on the enclosure ventilation system.

---

10. Critical PE Exam Traps & Pitfalls

Trap 1: Forgetting Absolute Temperatures ($T^4 - T_{surr}^4$)
Never evaluate radiative heat exchange using Celsius ($^\circ\text{C}$) or Fahrenheit ($^\circ\text{F}$). Always convert to Kelvin ($K = ^\circ\text{C} + 273.15$) or Rankine ($^\circ\text{R} = ^\circ\text{F} + 459.67$). Furthermore, remember that $T_1^4 - T_2^4 \neq (T_1 - T_2)^4$; substituting $(T_1 - T_2)^4$ underestimates heat transfer by many orders of magnitude.

Trap 2: Confusing Small Object in Large Enclosure with Parallel Plates
If an exam question describes a hot pipe or small tank located in a large mechanical room or furnace enclosure, use $q = \epsilon_1 \sigma A_1 (T_1^4 - T_{surr}^4)$. Do NOT use the parallel plate denominator $(1/\epsilon_1 + 1/\epsilon_2 - 1)$, because the large enclosure acts as a blackbody cavity and $\epsilon_2$ is irrelevant.

Trap 3: View Factor Reciprocity Direction
Always remember $A_1 F_{12} = A_2 F_{21}$. If surface 1 is a small plate and surface 2 is a large wall, $F_{12}$ might be $0.80$, but $F_{21} = (A_1 / A_2) F_{12}$ will be much smaller. Confusing the indices produces massive errors in energy exchange.

Trap 4: Multi-Shield Reduction Fallacy ($1/(N+1)$ vs. $1/2^N$)
A common blunder is assuming that each successive radiation shield halves the heat transfer (yielding $1/2^N$). The exact analytical relationship for $N$ shields of identical emissivity is $\mathbf{1 / (N + 1)}$. For 3 shields, the reduction factor is $1/4 = 0.25$, not $1/8 = 0.125$.