schema_version: 1 name: spleen-c1-blade intent: >- Reconstruct one SPLEEN C1 turbine cascade blade as editable KCL. Build the closed airfoil profile from the attached coordinate table (sheet SPLEENC1_Coord: pressure side x,y in columns A-B and suction side x,y in columns C-D, both in metres, both running from the leading edge at the origin to the shared trailing-edge point), keeping the table's axes, origin, scale and orientation exactly: x axial, y pitchwise, leading edge at (0, 0), trailing edge at (47.614, -21.600) mm, so the chord sits at the documented 24.4 degree stagger. Extrude the profile straight along +z from z = 0 over the documented cascade span (165.0 mm, Table 2.1). Preserve the leading edge, the suction-side curvature and the trailing-edge closure as given; do not substitute a generic airfoil, do not smooth or re-fit the shape beyond what a faithful curve through the published points requires, and do not add a root, platform, fillets or a display stand. The coordinate table is authoritative over any CAD file (the database's v1 CAD had a wrong stagger angle). One solid; export STEP and STL. units: length: mm angle: deg material: null density_kg_m3: null process: null release_status: reconstruction frame: origin: >- The shared leading-edge coordinate in SPLEENC1_Coord cells A3:D3, at the starting span plane z = 0. This is (0, 0, 0) mm; it is a published boundary landmark, not the minimum-x point or the profile centroid. axes: x: >- Positive axial direction, exactly increasing spreadsheet x (columns A and C) after multiplication by 1000 to convert metres to millimetres. y: >- Positive pitchwise direction, exactly increasing spreadsheet y (columns B and D) after multiplication by 1000. The shared trailing edge has negative y. z: >- Positive span direction normal to the spreadsheet XY plane, completing a right-handed frame; extrude from z = 0 to z = 165.0 mm without twist or taper. datums: - name: spanStart description: >- Planar blade end at z = 0, outward normal -z; its leading-edge landmark fixes the origin and its sketch axes retain the spreadsheet x and y axes. - name: axialDatum description: >- Construction datum plane y = 0 containing the origin and the +x and +z directions. It fixes the axial direction without aligning the chord to x. - name: pitchwiseDatum description: >- Construction datum plane x = 0 containing the origin and the +y and +z directions. It is not tangent to the leading-edge nose. - name: chordDatum description: >- Line in z = 0 from (0, 0) to the exact shared coordinate (47.6144470215, -21.59972305301) mm in A1003:D1003. Its signed angle from +x toward +y is -24.40085023652175 deg, consistent with the rounded documented stagger magnitude 24.4 deg. No additional stagger rotation. - name: spanEnd description: Planar blade end at z = 165.0 mm, outward normal +z. envelope: min: [-0.19685863578579998, -21.6984059788506, 0.0] max: [47.77582706417, 9.51390836469706, 165.0] tolerance: 0.01 parameters: - name: span value: 165.0 unit: mm provenance: stated source: sources/spleen-c1-geometry-excerpt.md, Table 2.1, "Cascade span [mm] | 165.0" tolerance: 0.01 description: Straight extrusion length along +z; the starting plane remains z = 0. edit_test: delta: 10.0 expect: volume_delta: 2306.3711778179277 direction: increase tolerance_rel: 0.002 bbox_delta: [0.0, 0.0, 10.0] - name: axialChord value: 47.6144470215 unit: mm provenance: stated source: sources/SPLEENC1_Geometry_Airfoil_2D_v1.xlsx, SPLEENC1_Coord!A1003/C1003 and Features!B6 tolerance: 0.001 description: >- Shared trailing-edge x coordinate: 0.0476144470215 m in the coordinate table, and 47.6144470215 mm in Features. Retain all digits. At baseline, every source x coordinate is used unchanged after unit conversion. For the edit test, multiply every converted x by axialChord / 47.6144470215, holding every y coordinate, trailingEdgeY, and span fixed. This defines an axial-only edit about x = 0; it does not impose an additional rotation. edit_test: delta: 1.0 expect: volume_delta: 799.2348292276137 direction: increase tolerance_rel: 0.002 bbox_delta: [1.0075237391351841, 0.0, 0.0] - name: trailingEdgeY value: -21.59972305301 unit: mm provenance: stated source: sources/SPLEENC1_Geometry_Airfoil_2D_v1.xlsx, SPLEENC1_Coord!B1003/D1003 tolerance: 0.001 description: >- Shared trailing-edge y coordinate, from -0.02159972305301 m. Retain all digits. A deliberate edit scales converted y by trailingEdgeY / (-21.59972305301) about y = 0, independently of axialChord and span. Both coordinate scale factors equal one for the requested reconstruction. - name: trailingEdgeRadius value: 0.435 unit: mm provenance: stated source: sources/SPLEENC1_Geometry_Airfoil_2D_v1.xlsx, Features!A9:B9, "Trailing edge radius [mm]", 0.435 tolerance: 0.005 description: >- Published nominal trailing-edge radius; documentary cross-check on the supplied contour, not a fillet operation or permission to replace the terminal coordinate rows with a fitted circle. The coordinate table wins any discrepancy. This is a nominal reference constant, not an edit driver. - name: profilePerimeter value: 123.78447524923155 unit: mm provenance: measured (reference model) source: reference/profile.json tolerance: 0.05 description: >- measurements.perimeter: closed-loop sum of consecutive point distances, including the final segment to the leading edge. Nominal verification constant used for the analytic surface-area baseline, not a shape driver. - name: trueChord value: 52.284640202739865 unit: mm provenance: derived formula: sqrt(axialChord^2 + trailingEdgeY^2) tolerance: 0.001 description: >- Distance between the shared LE and TE landmarks. The workbook Features value 52.285 mm and Table 2.1 value 52.28 mm are rounded documentary cross-checks. Do not use the ingest's farthest-pair chord as this parameter. Nominal derived reference constant; it must not equality-lock edit drivers. - name: signedStagger value: -24.40085023652175 unit: deg provenance: derived formula: atan2(trailingEdgeY, axialChord) * 180 / pi tolerance: 0.005 description: >- Signed LE-to-TE chord angle measured from +x toward +y. Its magnitude rounds to the published 24.4 deg. It documents the orientation already present in the coordinates; never rotate the nominal profile by this angle again. Nominal derived reference constant, not an equality lock. features: - id: closedAirfoil kind: profile count: 1 description: >- One closed airfoil boundary from all published coordinate rows. Trace PS A3:B1003 from LE to TE, then SS C1002:D4 in reverse toward LE, and close once at the original LE. Each side has 1001 points; shared endpoints yield 2000 distinct loop vertices. Preserve every point and side identity. A faithful through-point curve is permitted; smoothing, point reduction, generic-airfoil substitution and reference-CAD imports are forbidden. Nominal source-point-to-boundary error must be at most 0.001 mm; this additional pointwise requirement needs verification beyond schema probes. parameters: [axialChord, trailingEdgeY, trueChord, signedStagger, profilePerimeter] verify: - method: bbox note: Full table extrema; LE and TE landmarks are not the bounding-box extrema. - method: section section: midSpan - method: count section: midSpan count: 1 note: One outer boundary, zero holes; acceptance.solid_count separately requires one solid. - method: solid points: [[10.0, 6.0, 82.5], [25.0, 3.0, 82.5], [40.0, -12.2, 82.5]] - method: void points: [[20.0, 0.0, 82.5], [25.0, 7.0, 82.5]] note: Exterior clear-space probes on opposite sides of the blade; these do not specify cavities. - id: pressureSide kind: profile count: 1 description: >- Pressure-side boundary portion of closedAirfoil, exactly columns A-B from row 3 through row 1003; preserve its curved contour and side identity along the full span. This is not an additional solid. parameters: [axialChord, trailingEdgeY] verify: - method: section section: axialCrown - method: solid points: [[30.0, -3.0, 82.5], [40.0, -13.0, 82.5]] - method: void points: [[25.0, -1.0, 82.5]] note: Exterior of the pressure side. - id: suctionSide kind: profile count: 1 description: >- Suction-side boundary portion of closedAirfoil, exactly columns C-D from row 3 through row 1003, traversed backward when closing the loop. Preserve the pronounced crown, nose curvature and terminal curvature. parameters: [axialChord, trailingEdgeY] verify: - method: bbox note: In particular retain y_max = 9.51390836469706 mm. - method: section section: axialCrown - method: solid points: [[14.0, 9.3, 82.5]] - method: void points: [[14.0, 9.7, 82.5]] note: Exterior of the suction-side crown. - id: leadingEdge kind: profile count: 1 description: >- The sides meet at the published origin (0, 0) and retain the surrounding rounded nose, including negative-x coordinates. No leading-edge radius is invented and no tangent-plane relocation is allowed. parameters: [axialChord, trailingEdgeY] verify: - method: bbox note: Retain x_min = -0.19685863578579998 mm despite the LE landmark at x = 0. - method: section section: axialLeadingEdge - method: solid points: [[-0.1, 0.5, 82.5], [0.1, 0.4, 82.5]] - method: void points: [[-0.3, 0.7, 82.5], [-0.05, -0.2, 82.5]] note: Exterior points bracket the nose. - id: trailingEdge kind: profile count: 1 description: >- Close the PS/SS terminal arcs at the exact shared table point (47.6144470215, -21.59972305301) mm. Preserve all nearby coordinate rows and the table's rounded edge, including its extrema beyond that landmark. The documented 0.435 mm radius is retained as a cross-check; add no independent circular cap, bevel, gap, blunt truncation or fillet. parameters: [axialChord, trailingEdgeY, trailingEdgeRadius] verify: - method: bbox note: Retain x_max = 47.77582706417 and y_min = -21.6984059788506 mm. - method: section section: axialTrailingEdge - method: count section: axialTrailingEdge count: 1 - method: solid points: [[47.55, -21.3, 82.5]] - method: void points: [[47.9, -21.3, 82.5]] note: Exterior of the rounded trailing edge. - id: straightSpan kind: extrude count: 1 description: >- Extrude the complete closedAirfoil straight from z = 0 through +165.0 mm. The XY profile is constant at every span station: one solid, no twist, taper, holes, cavities, root, platform, added fillets or display stand. parameters: [span, axialChord, trailingEdgeY] verify: - method: bbox - method: section section: nearSpanStart - method: section section: midSpan - method: section section: nearSpanEnd - method: count section: nearSpanStart count: 1 - method: count section: nearSpanEnd count: 1 - method: solid points: [[25.0, 3.0, 1.0], [25.0, 3.0, 164.0]] - method: face face: spanStart - method: face face: spanEnd - id: planarEndCaps kind: other count: 2 description: Two planar airfoil-shaped caps created by the extrusion, at z = 0 and z = span. parameters: [span, axialChord, trailingEdgeY] verify: - method: face face: spanStart - method: face face: spanEnd interfaces: - name: sourceFrame description: >- Preserve the table's LE origin, axial/pitchwise axes, signed stagger and metre-to-millimetre scale in KCL and both exports. No centering or presentation rotation. must_not_change: true - name: pressureSide description: >- Retain traceable pressure-side wall identity from columns A-B, including all wall faces if the curve representation creates multiple faces. must_not_change: true - name: suctionSide description: >- Retain traceable suction-side wall identity from columns C-D, including all wall faces if the curve representation creates multiple faces. must_not_change: true - name: spanCaps description: >- Keep named planar end faces spanStart (z = 0, outward -z) and spanEnd (z = span, outward +z). This blade has no inlet/outlet flow-domain faces and no root or platform mating interface. must_not_change: true acceptance: bbox_tolerance: 0.01 volume: expected: 38055.12443399581 tolerance_rel: 0.002 provenance: derived note: >- A = reference/profile.json measurements.area = 230.63711778179277 mm^2, the closed-point-loop shoelace area. V = A * span. At baseline span = 165. For the independent edits, DeltaV_span = A * DeltaSpan and DeltaV_axialChord = A * span * DeltaAxialChord / 47.6144470215, with all y coordinates fixed. Center-of-mass formula (the schema has no center_of_mass.note field): for consecutive points p_i=(x_i,y_i), closing cyclically, d_i=x_i*y_(i+1)-x_(i+1)*y_i, A_poly=0.5*sum(d_i), Cx=sum((x_i+x_(i+1))*d_i)/(6*A_poly), Cy=sum((y_i+y_(i+1))*d_i)/(6*A_poly), Cz=span/2. Use area moments, not measurements.centroid, which is only a vertex mean. Blockout is the same envelope-only airfoil extrusion, with band [0.99*A*span, 1.01*A*span]. surface_area: expected: 20885.71265168679 tolerance_rel: 0.002 provenance: derived note: >- S = 2*A + profilePerimeter*span, with A = 230.63711778179277 mm^2 from reference/profile.json measurements.area. Two caps plus all extruded boundary walls. This polygonal reference baseline permits only small interpolation differences within the stated digital tolerance. center_of_mass: expected: [20.619657984838426, 1.0449253890203034, 82.5] tolerance: 0.01 provenance: derived solid_count: 1 sections: - id: nearSpanStart plane: z at: 16.5 expect: area: 230.63711778179277 area_tolerance_rel: 0.002 loops: 1 holes: 0 description: >- At span/10, expose the full closed airfoil; A from measurements.area. One outer loop and no inner loops. - id: midSpan plane: z at: 82.5 expect: area: 230.63711778179277 area_tolerance_rel: 0.002 loops: 1 holes: 0 description: At span/2, the same full airfoil area A and topology. - id: nearSpanEnd plane: z at: 148.5 expect: area: 230.63711778179277 area_tolerance_rel: 0.002 loops: 1 holes: 0 description: At 9*span/10, the same full airfoil area A and topology; detect taper or twist. - id: axialLeadingEdge plane: x at: 0.1 expect: area: 306.8773636067 area_tolerance_rel: 0.01 loops: 1 holes: 0 description: >- Leading-edge diagnostic rectangle in yz. Linear intersection of reference/profile.json points_mm gives y in [-0.1007751328722282, 1.7590876768653476] mm; area = their difference * span. - id: axialCrown plane: x at: 14.0 expect: area: 1061.785915064893 area_tolerance_rel: 0.01 loops: 1 holes: 0 description: >- Pressure/suction-side crown diagnostic rectangle in yz. Intersections of points_mm give y in [3.0780356493613352, 9.513101801269778] mm; area = their difference * span. - id: axialTrailingEdge plane: x at: 47.6 expect: area: 120.18396505371327 area_tolerance_rel: 0.01 loops: 1 holes: 0 description: >- Terminal closure diagnostic rectangle in yz. Intersections of points_mm give y in [-21.610116599844556, -20.881728932852354] mm; area = their difference * span. faces: - name: spanStart plane: z at: 0.0 normal: '-' area: 230.63711778179277 area_tolerance_rel: 0.002 tolerance: 0.01 center: [20.619657984838426, 1.0449253890203034] - name: spanEnd plane: z at: 165.0 normal: '+' area: 230.63711778179277 area_tolerance_rel: 0.002 tolerance: 0.01 center: [20.619657984838426, 1.0449253890203034] deviation: null blockout: volume_min: 37674.57318965585 volume_max: 38435.67567833576 export_volume_tolerance_rel: 0.002 references: - path: sources/SPLEENC1_Geometry_Airfoil_2D_v1.xlsx kind: table role: authoritative sha256: eb02e45c1ff8b6f94fcb7a91209f5b0113c96b1ffa27f9cbaff18133cb37a4f2 units: m in SPLEENC1_Coord; mm and deg in Features revision: Coordinate workbook v1; cited by SPLEEN database v5 as correct note: >- SPLEENC1_Coord rows 3:1003, A-B pressure side and C-D suction side, both LE to TE. Features cells B4/B6:B9 give documentary angle, chords, pitch and TE radius. Workbook coordinates take precedence over rounded text and any CAD geometry, including the known wrong-stagger v1 CAD. - path: sources/spleen-c1-geometry-excerpt.md kind: text role: authoritative sha256: f3e30892ac891e29e7b6483e6456b6d7e2364fdf719a08a28e0f13ada6fc18e8 units: mm and deg; coordinate commentary also uses m revision: Database v5; Geometry_TestSection_Info_v2 Table 2.1; v2 update dated 25/11/2022 note: >- Supplies the 165.0 mm blade span and documentary cascade parameters; quotes the correction identifying the coordinate workbook as correct. Source attribution is recorded in the excerpt; original PDFs/CAD are not supplied. The 225 mm upstream test-section height is not blade span. - path: reference/profile.json kind: reference-model role: authoritative sha256: 0566d60bccac41d4dcbb77698128b45c40ce94b7256b153278998cc265e371e7 units: mm, mm^2 and deg revision: Deterministic profile ingest generated 2026-09-15T17:56:12Z note: >- Derived numerical reference subordinate to the workbook. Use points_mm, measurements.area, perimeter, bbox_min, bbox_max and size for nominal verification. Verified point-for-point against the converted workbook. measurements.chord and stagger_deg describe the farthest vertex pair, not the shared LE/TE chord; measurements.centroid is an unweighted boundary-vertex mean, not the area centroid. Exclude those three fields from physical chord/stagger/COM acceptance. No mesh or suggested tolerances are present. closed_input=false means the final LE vertex is not repeated; cyclic closure is required. The polygon was independently checked for validity because self_intersections_checked=false. - path: reference/profile.png kind: image role: illustrative sha256: 882cb4e073a2d8c3fb8beab93ed9095e96565fffff2ad9ef81c1596dde6d75dd units: Pixels rendering the mm profile at approximately 17.509964 pixels/mm revision: Plot accompanying the 2026-09-15T17:56:12Z profile ingest note: >- 900 by 606 pixel undimensioned plan-view plot of the same loop; used only for visual orientation and feature evidence. No dimensions were inferred from raster pixels. open_questions: - >- What material, density and manufacturing process, if any, should be assigned? The supplied sources establish geometry only; these fields remain null and no mass claim is made. - >- Is a specific original interpolation law required between published points? No spline degree, knot vector or continuity convention is supplied. The reconstruction must retain every point within 0.001 mm and preserve the contour without smoothing; exact between-point authoring geometry remains unspecified.