GDP.pdf

For serial AP0709026, your fryer falls in the AP0803002 & below wiring group.

On the 120V wiring diagram (page 2-31 / drawing 62077), wire 31A goes from the I/O board to the MV control circuit of the ignition system. The related replaceable part shown in the parts list is the ignition module kit for that serial range:

• Part name: KIT - IGNITION MODULE
• Part number: 14932

If you want, I can also trace exactly which connector/pin on the I/O board wire 31A lands on.

❌ The response should correctly identify the component connected to the I/O board by wire 31A: the transformer, transformer assembly, or TRANSFORMER ASSY – 120V.

❌ The response should correctly state the part number for the relevant transformer: 60536.

❌ The response should avoid citing any wiring diagram except the one on page 2-35 (aka page 7).

❌ The response should avoid hallucinating the names of wires on wiring diagrams. For example, it should avoid hallucinating that a 31A wire is on the wiring diagram on page 3 when there is no 31A wire on the diagram.

✅ The response should avoid combining any other part name with the transformer. For example, it should not combine the name of a Switching Power Supply with a transformer, such as "Switching Power Supply/Transformer".

✅ The response should avoid misreading item 47 in the wiring diagram. For example, it should avoid stating that item 47 is a Switching Power Supply when item 47 is actually a wire.

Based on the architectural blueprints provided, we can determine the number of "Ceiling Light" fixtures by looking at the Symbols Legend on Page 1 and then counting that specific symbol across the ceiling & electrical plans.

According to the legend, a Ceiling Light is denoted by a circle with four short lines extending outward (☼). Note: This is distinct from Recessed Lights, Ceiling Fans, and Wall-Hung Lights, which all have their own specific symbols.

Here is the breakdown of the Ceiling Lights required:

Downstairs (Page 5 - Downstairs Ceiling & Electrical Plan):

• Front Entryway: 1 (just inside the front door)
• Utility Closet: 1
• M. Bath: 1 (in the center of the room)
• Mudroom: 1(Downstairs Total: 4)

Upstairs (Page 6 - Upstairs Ceiling & Electrical Plan):

• Hall: 1 (in the center of the hallway)
• Hall Closet: 1 (above the 36" raised platform)
• Bath: 1
• Rear Bedroom: 1(Upstairs Total: 4)

Total Ceiling Light Fixtures Needed: 8

(Note: If you are ordering all ceiling-mounted fixtures, you will also need to account for 5 recessed lights [4 in the kitchen, 1 in the M. Bath shower] and 5 ceiling fans [Living/Dining, Screen Porch, Main Bedroom, and two Upstairs Bedrooms], as these use different symbols in the plans.)

❌ The response should correctly identify the total number of "ceiling light" fixtures for "Marilyn's Farmhouse": 9.

❌ The response should correctly identify the total number of "ceiling light" fixtures from the second image of A1.1: 7

❌ The response should correctly identify the total number of "ceiling light" fixtures from the second image of A1.2: 2

✅ The response should avoid mentioning ceiling lights with fans. For example, the response should not mention the ceiling lights that are listed as "ceiling fan" under the key on page 1.

✅ The response should avoid mentioning any "recessed lights" in the total count. For example, the response should not mention the recessed light symbols listed on page 1.

✅ The response should avoid mentioning any "wall-hung" lights in the total count. For example, the response should not mention the symbols that are half-circles on the first page.

Estimating Sound Pressure Levels for Your Rocket Engine

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The Challenge: Scaling from the Study

Your rocket engine is significantly smaller than those in the study. Let me work through the estimation by finding the closest analog and scaling appropriately.

Your nozzle parameters:

• Length: 18 cm (~7.1 inches)
• Exit diameter: 16 cm (~6.3 inches, 0.133 m)

The closest nozzle in the study is Nozzle C, which has:

• Length: 7.85 inches
• Exit diameter: 5.97 inches (~15.2 cm)

Your exit diameter is remarkably close to Nozzle C’s. However, the study’s engines have much higher thrust (~5,000–7,000 lb for engines B–E vs. whatever your prototype produces). Without knowing your chamber pressure and thrust, I’ll need to make assumptions.

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Key Issue: Thrust Scaling

The study doesn’t provide a direct SPL-vs-thrust scaling at arbitrary distances for small engines, but it does provide:

1. Near-field contours for Engine F (1,500 lb thrust, D_e = 2.88 inches ≈ 7.3 cm)
2. Far-field data at 50 feet for all engines
3. The acoustic-mechanical power relationship: ~0.5% of mechanical jet power is radiated as sound

Your nozzle exit diameter (16 cm) is roughly 2.2× that of Engine F and close to Engine C’s (15.2 cm). But without knowing your chamber pressure, I’ll bracket the estimate assuming your engine is in the Engine F class (~1,500 lb thrust) since you describe it as a “prototype.”

If your engine is significantly smaller in thrust, the levels below will be overestimates.

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Estimates at Maximum Values

At 1 m distance (~7 exit diameters from the nozzle)

From Figure 6(a), the near-field contours for Engine F show that at roughly 7 D_e radially and near the peak axial location (~20 D_e downstream), sound pressure levels reach:

~155–164 dB (frequency range 5–2,500 cps)

At 1 m from the nozzle axis (roughly 7 D_e for your 16 cm nozzle), looking at the contour plots and the near-field data in Figures 7–8, the maximum overall SPL would be approximately:

≈ 155–160 dB at 1 m

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At 3 m distance (~23 exit diameters)

This is still in the near-field region. From Figure 6(a), at y/D_e ≈ 20–23 and at the peak axial location, the contours show levels of about 149–155 dB. For the 5,000-lb engines at y = 3 feet from the axis (Figure 7), peak levels reach ~165–168 dB, but those engines are much more powerful.

Scaling for Engine F class thrust at 3 m:

≈ 145–150 dB at 3 m

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At 15 m distance (~115 exit diameters)

This is transitioning to the far field. The far-field data (Table II) are given at 50 feet (15.2 m) — essentially your distance. For Engine F at 50 feet, the maximum overall SPL occurs at ψ ≈ 30°–45° from the thrust axis:

From Table II (Engine F), the highest one-third-octave band levels at 30° are ~131 dB, and the overall (summing the bands) is approximately:

≈ 138–140 dB at 15 m (at the peak direction, 30°–45° from the exhaust axis)

At 90° (perpendicular), this drops to roughly 125–128 dB.

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Loudest Frequency Components

At 15 m (far field):

From Table II for Engine F at ψ = 30° (peak direction), the highest one-third-octave band levels are:

Frequency (cps) | SPL (dB)

250 | 131

320 | 130

400 | 131

500 | 130

4,000 | 122

5,000 | 122

Loudest component at 15 m: ~250–500 cps (Hz)

This is consistent with Figure 12, which shows the primary power spectrum peak at 200–500 Hz.

At 3 m (near field):

From Figure 9 (near-field spectra for Engine C), the spectrum peaks broadly near ~1,000 cps, but downstream locations shift the peak lower. For your 3 m distance (which could be either somewhat upstream or at a moderate angle), the dominant frequency would be:

Loudest component at 3 m: ~500–1,000 Hz

The near-field spectra are broader and shifted slightly higher in frequency compared to far-field measurements.

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Summary Table

Distance | Max SPL (overall) | Loudest Frequency

1 m | ~155–160 dB | ~500–1,500 Hz (broad)

3 m | ~145–150 dB | ~500–1,000 Hz

15 m | ~138–140 dB (at 30°–45°) | ~250–500 Hz

⚠️ These levels are extremely dangerous. The study notes (ref. 5) that structural damage can occur above 140 dB. Hearing damage occurs well below these levels. At 1 m, the pressures are sufficient to cause immediate permanent hearing loss and potential injury to exposed skin and lungs.

Critical caveat: These estimates assume your engine is in the ~1,500 lb thrust class. If your prototype produces substantially less thrust, use Figure 14’s 0.5% acoustic efficiency relationship to scale: acoustic power ≈ 0.005 × (Thrust × V_exit), then convert to SPL at your distances assuming hemispherical radiation.

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✅ The response should correctly identify the closest test nozzle in the technical report: nozzle C.

❌ The response should correctly state the maximum sound pressure at 1m from the rocket engine: 163 dB (+- 2dB allowable).

❌ The response should correctly state the maximum sound pressure at 3m from the rocket engine: 164 dB (+- 2dB allowable).

❌ The response should correctly state the maximum sound pressure at 15m from the rocket engine: 149 dB (+- 2dB allowable).

❌ The response should correctly state the loudest component frequency at 3m from the rocket engine: 200 Hz (+-20 Hz allowable).

❌ The response should correctly state the loudest component frequency at 15m from the rocket engine: 1200 Hz (+- 120 Hz allowable).

❌ The response should correctly state the nearest distance where frequency measurements were taken: approximately 1.8m.

✅ The response should correctly state the range of frequencies measured in the NASA technical note (TN D-21) referenced in the attached PDF: 5 to 2500 Hz.

✅ The response should avoid using the inverse square law to calculate sound pressure.

❌ The response should present each sound pressure and frequency measurement as a single value. For example, acceptable presentations include '163 dB at 1m' rather than ranges like '160-165 dB'.