1. A storm water filtration system comprising:
an inlet grate and a filtration device; said filtration device contacting a portion of said inlet grate; said filtration device further comprising: a mat adapted to filter ground water said mat having a top, a bottom, at least a side, and a main filtering portion, said main filtering portion comprising randomly-aligned coir fibers and a latex binding agent, and having a density between 2.5 and 4.5 oz.sq. ft., wherein said density of said main filtering portion allows water to flow generally unimpeded through said main filtering portion while sediment is filtered, a portion of said sediment being filtered immediately upon contacting said main filtering portion and a portion of said sediment being filtered within said main filtering portion, whereby said filtration device may be cleaned and reused without removing said filtration device from said inlet grate.
2. The storm water filtration system of claim 1, wherein said filtration device is removably affixed to said inlet grate.
3. The storm water filtration system of claim 2, wherein said filtration device is positioned above said inlet grate.
4. The storm water filtration system of claim 3, wherein said filtration device is removably affixed and cover the entire area of said inlet grate.
5. The storm water filtration system of claim 4, wherein said filtration device is used on a convex inlet grate.
6. The storm water filtration system of claim 4, further comprising a curb adjacent said inlet grate, wherein said filtration device is removably affixed to said inlet grate and said filtration device is further placed over a portion of said curb.
7. The storm water filtration system of claim 4, wherein said latex binding agent is the only binding agent present in said filtering portion.
8. A storm water filtration system comprising:
an inlet grate and a filtration device; said filtration device contacting a portion of said inlet grate;
said filtration device further comprising, a mat adapted to filter ground water, said mat having a top, a bottom, at least a side, and an upper filtering portion and a lower filtering portion, wherein said upper filtering portion has a density between 4.5 and 6 oz. sq. ft and said lower filtering portion has a density between 3.0 and 4.5 oz.sq. ft, said upper and said lower filtering portions being made from randomly aligned fibers and a binding agent, whereby said upper filtering portion may be driven over by vehicle and maintain its function and whereby said filtration device may be cleaned and reused without removing said filtration device from said inlet grate.
9. The storm water filtration system of claim 8, wherein said randomly aligned fibers are made of natural fibers.
10. The storm water filtration system of claim 9, wherein said fibers are coir fibers.
11. The storm water filtration system of claim 10, wherein said binding agent is a latex binding agent.
12. The storm water filtration system of claim 11 wherein said upper filtering portion has a density between 4.75 and 5.5 oz. sq. ft. and said lower filtering portion has a density between 3.25 and 4.0 oz.sq. ft.
13. The storm water filtration system of claim 12, wherein said filtration device is removably affixed to said inlet grate.
14. The storm water filtration system of claim 13, wherein said inlet grate and filtration device may be removed for cleaning as a single unit.
The claims below are in addition to those above.
All refrences to claim(s) which appear below refer to the numbering after this setence.
1. A turbine engine comprising:
a rotor comprising:
a plurality of disks, each disk extending radially from an inner aperture to an outer periphery;
a plurality of stages of blades, each stage borne by an associated one of said disks; and
a plurality of spacers, each spacer between an adjacent pair of said disks; and
a stator comprising a plurality of stages of vanes, the vanes of at least a first of said stages of vanes having airfoils with:
inboard tips in facing proximity to an outer surface of a first of said spacers; and
a dihedral and sweep profile characterized by at least one of:
leading edge sweep of 25-45\xb0 along a first region of at least 10% of total span starting within 5% of the tip; and
dihedral of 30-60\xb0 along a second region of at least 10% of total span starting within 5% of the tip.
2. The engine of claim 1 having both said leading edge sweep and said dihedral.
3. The engine of claim 1 wherein:
said dihedral is 35-55\xb0 along said second region.
4. The engine of claim 1 wherein:
said leading edge sweep is 30-40\xb0 along said first region.
5. The engine of claim 1 wherein:
along a majority of the total span, the airfoil extends within 10\xb0 of radially.
6. The engine of claim 1 wherein:
said first region is 20-40% of the total span.
7. The engine of claim 1 wherein:
said first spacer has a longitudinal cross-section, said longitudinal cross-section having a first portion being essentially outwardly concave in a static condition; and
a central shaft carries the plurality of disks and the plurality of spacers to rotate about an axis with the plurality of disks and the plurality of spacers.
8. The engine of claim 1 wherein:
the first stage of vanes is between an upstream-most one and a next one of said plurality of stages of blades.
9. The engine of claim 1 wherein:
the inboard tips of the first stage of vanes are longitudinally convex.
10. The engine of claim 1 wherein:
in a stationary condition, the inboard tips of the first stage of vanes are within 1 cm of an outboard surface of the first spacer along.
11. The engine of claim 1 wherein:
the plurality of disks are high speed compressor section disks.
12. A gas turbine engine stator component comprising:
a shroud or a shroud segment;
at least one airfoil unitarily formed with or secured to the shroud or shroud segment and having:
leading and trailing edges;
pressure and suction sides;
a proximal outboard root;
a distal inboard tip; and
a dihedral and sweep profile characterized by at least one of:
leading edge sweep of 25-45\xb0 along a first region of at least 10% of total span starting within 5% of the tip; and
dihedral of 30-60\xb0 along a second region of at least 10% of total span starting within 5% of the tip.
13. The stator component of claim 12 having both said leading edge sweep and said dihedral.
14. The stator component of claim 12 wherein:
the shroud or shroud segment and the at least one airfoil are unitarily-formed as a single piece of a metallic material.
15. A turbine engine vane element comprising:
an outboard shroud having outboard and inboard surfaces the inboard surface being concave in a first direction so as to essentially define a longitudinal axis of curvature; and
an airfoil element having:
a root at the shroud inboard surface;
a tip; and
a dihedral and sweep profile characterized by:
leading edge sweep of 25-45\xb0 along a first region of at least 10% of total span starting within 5% of the tip; and
dihedral of 30-60\xb0 along a second region of at least 10% of total span starting within 5% of the tip.
16. The element of claim 15 wherein:
said first region is 20-40% of the total span.
17. A plurality of elements of claim 15 assembled to form a vane stage.
18. For a gas turbine engine configuration comprising:
a rotor stack comprising:
a plurality of disks, each disk extending radially from an inner aperture to an outer blade-bearing periphery; and
a plurality of spacers, each spacer between an adjacent pair of said disks;
a plurality of vane stages interspersed with the disks; and
a shaft carrying the rotor stack,
a method for engineering the engine configuration comprising:
for at least a first of said vane stages varying a dihedral and sweep distribution to a final distribution characterized by:
leading edge sweep of 25-45\xb0 along a first region of at least 10% of total span starting within 5% of the tip; and
dihedral of 30-60\xb0 along a second region of at least 10% of total span starting within 5% of the tip.
19. The method of claim 18 performed as a simulation.
20. The method of claim 18 wherein the varying achieves a reduction in total pressure loss along a third region of at least 20% of the total span and starting within 10% span from the tip.
21. The method of claim 18 performed as a reengineering of the engine configuration from an initial configuration to a reengineered configuration wherein:
the reengineered configuration provides a reduction in loss relative to the initial configuration.
22. The method of claim 18 performed as a reengineering of an engine configuration from an initial configuration to a reengineered configuration wherein:
the initial configuration has at a dihedral and sweep profile characterized by:
leading edge sweep less than of 20\xb0 along a majority of said first region; and
dihedral of less than 30\xb0 along a said second region.
23. The method of claim 18 performed as a reengineering of an engine configuration from an initial configuration to a reengineered configuration wherein:
relative to the initial configuration the reengineered configuration provides removes inboard platforms from the vanes of the first vane stage.
24. The method of claim 18 performed as a reengineering of an engine configuration from an initial configuration to a reengineered configuration wherein:
relative to the initial configuration the reengineered configuration provides a reduced average tip-to-rotor gap.