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Fri, 26 Jun 2020 06:19:30 +0000 To: Rotary motors in aircraft Subject: Re: [FlyRotary] Re: BSFC change on staging Thread-Topic: [FlyRotary] Re: BSFC change on staging Thread-Index: AQHWS2uwcKWNBJjiWkCPiwFTMkkVdKjqYET+ Date: Fri, 26 Jun 2020 06:19:30 +0000 Message-ID: References: In-Reply-To: Accept-Language: en-US Content-Language: en-US X-MS-Has-Attach: X-MS-TNEF-Correlator: authentication-results: lancaironline.net; dkim=none (message not signed) header.d=none;lancaironline.net; dmarc=none action=none header.from=uwyo.edu; x-originating-ip: [98.127.87.75] x-ms-publictraffictype: Email x-ms-office365-filtering-correlation-id: 8a9f6ade-7864-4a3d-7ca4-08d81998e2b5 x-ms-traffictypediagnostic: CY4PR0501MB3841: x-microsoft-antispam-prvs: x-ms-oob-tlc-oobclassifiers: OLM:10000; x-forefront-prvs: 0446F0FCE1 x-ms-exchange-senderadcheck: 1 x-microsoft-antispam: BCL:0; x-microsoft-antispam-message-info: cVpDFDyY6Ui0+ne2QC7jJGOLII8RUvWdyqryrkxFAJHde+NG+JNuXi1KlNcokMHmhifGiBii8kQ/rv2NKPScWiZ5RzYgUdFCinpoBdO2UgjY4ewV+2dhmpZZXXGO6XxHu0x4/WU8ISMXiMoYJP5C9EuuwmT7wQvdoTYRKPh2PcOljCAZnUn6kQ5G5XWjDyoekN6HctfhpISRup1KjeDXMm9FZR//qNMKdVAPh35cTsFzjKENaR33TgOdXq1V9u/3zB9Vf/GgFWAFme0ish3kGA7Rx99svqYQ+HCuQ1zldzcG5Y3XQqQySTYsoo8g/G9wOmNh8GJbyyGPxhWWuhVyR7NeUjteAQWU1Vy37AFddYAerG8D4XBW0XoivU88KXFywDs238vjhHNl8vTstA+2OA== x-forefront-antispam-report: CIP:255.255.255.255;CTRY:;LANG:en;SCL:1;SRV:;IPV:NLI;SFV:NSPM;H:CY4PR05MB3384.namprd05.prod.outlook.com;PTR:;CAT:NONE;SFTY:;SFS:(4636009)(366004)(396003)(346002)(39860400002)(376002)(136003)(279900001)(166002)(186003)(83380400001)(6506007)(316002)(53546011)(7696005)(786003)(33656002)(71200400001)(26005)(5660300002)(52536014)(966005)(19627405001)(6916009)(9686003)(478600001)(2906002)(55016002)(91956017)(75432002)(86362001)(66946007)(66476007)(66556008)(8936002)(8676002)(66446008)(64756008)(76116006);DIR:OUT;SFP:1102; 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charset="iso-2022-jp" Content-Transfer-Encoding: quoted-printable Steve, BSFC is calculated from the HP and the fuel flow. The HP is calculated from the torque and the RPM. The engine is mounted o= n ball bearings so it can rotate on the axis of the eccentric shaft. That = rotation is constrained with a 1 ft arm connected to a load cell calibrated= in lb. That gives torque in ft lb. Torque in ft lb multiplied by RPM and= divided by 5252 gives HP. Fuel flow is measured with a Floscan transducer calibrated in gal/hr. The g= al/hr multiplied by 6.17 lb/US gal, gasoline gives lb/hr. Fuel flow in lb/hr divided by HP gives BSFC in lb/(HP hr). My EC2's are earlier version (SN 200-499) updated in early 2010 where Mode = 7 allows setting the staging threshold. The Renesis engine is fitted with = a second CAS and a replacement trigger wheel with 12 teeth for the original= CAS and one tooth for the added CAS. This allows interchangeability with m= y flying 1986 13B which has a stock CAS. Your estimate of fuel saving due to a BSFC change of 0.5 is correct. Unfor= tunately, the observed BSFC change was about 0.05 rather than 0.5. Ed Anderson once told me that as a scientist, I collect data, but it takes = an engineer to determine what the data means. (He was smiling when he said= that). Your guess as to the reason for the BSFC change is as good or bett= er than mine. Steve Boese ________________________________ From: Rotary motors in aircraft on behalf of = Stephen Izett stephen.izett@gmail.com Sent: Thursday, June 25, 2020 9:41 PM To: Rotary motors in aircraft Subject: [FlyRotary] Re: BSFC change on staging =1B$B"!=1B(B This message was sent from a non-UWYO address. Please exercise= caution when clicking links or opening attachments from external sources. Hi there Steve Thanks for your work here. How do you measure the BSFC? So you have a version of the EC software where you can still change the Sta= ging point MAP. The BSFC is ~0.5 better unstaged. Is this due to better fuel-air mixing or = is something else at play? Am I right in thinking that at an economy cruise, a BSFC change of 0.5 migh= t yield an approx 0.9G/hr ($5/hr) of fuel saving. That might then argue for a Staging Point at the earlier 15.5=1B$B!I=1B(B M= AP to enable unstaged cruise rather than the locked in 20=1B$B!I=1B(B MAP o= f the current software version. What is your thoughts and conclusion if you have reached any? Thanks again Steve Steve Izett > On 26 Jun 2020, at 8:47 am, Steven W. Boese SBoese@uwyo.edu wrote: > > I ran a test on my engine stand with staged and unstaged fuel injectors b= ut with the same fuel flow and MAP. The results are shown in the attached = image. The engine is a 2010 2nd generation Renesis 6 port from an automati= c transmission car with the high RPM ports blocked off and stock fuel injec= tors. The reduction drive ratio is 3.18:1. The prop is a 3 blade 72" Warp= Drive and was operating just below stalled RPM. A turbo is installed but = no boost was used in the test. No attempt was made to operate at minimum B= SFC. > > Steve Boese > -- > Homepage: http://www.flyrotary.com/ > Archive and UnSub: http://mail.lancaironline.net:81/lists/flyrotary/Lis= t.html -- Homepage: http://www.flyrotary.com/ Archive and UnSub: http://mail.lancaironline.net:81/lists/flyrotary/List.= html --_000_CY4PR05MB3384C4B4A859CDEB7AFC9012B9930CY4PR05MB3384namp_ Content-Type: text/html; charset="iso-2022-jp" Content-Transfer-Encoding: quoted-printable
Steve,

BSFC is calculated from the HP and the fuel flow. 
 
The HP is calculated from the torque and the RPM.  The engine is= mounted  on ball bearings so it can rotate on the axis of the eccentr= ic shaft.  That rotation is constrained with a 1 ft arm connected to a= load cell calibrated in lb.  That gives torque in ft lb.  Torque in ft lb multiplied by RPM and divided by 5252 give= s HP.

Fuel flow is measured with a Floscan transducer calibrated in gal/hr.= The gal/hr multiplied by 6.17 lb/US gal, gasoline gives lb/hr.

Fuel flow in lb/hr divided by HP gives BSFC in lb/(HP hr).

My EC2's are earlier version (SN 200-499) updated in early 2010 where= Mode 7 allows setting the staging threshold.  The Renesis engine is f= itted with a second CAS and a replacement trigger wheel with 12 teeth for t= he original CAS and one tooth for the added CAS. This allows interchangeability with my flying 1986 13B which ha= s a stock CAS.

Your estimate of fuel saving due to a BSFC change of 0.5 is correct.&= nbsp; Unfortunately, the observed BSFC change was about 0.05 rather than 0.= 5.

Ed Anderson once told me that as a scientist, I collect data, but it = takes an engineer to determine what the data means.  (He was smiling w= hen he said that).  Your guess as to the reason for the BSFC change is= as good or better than mine.

Steve Boese    

From: Rotary motors in airc= raft <flyrotary@lancaironline.net> on behalf of Stephen Izett stephen= .izett@gmail.com <flyrotary@lancaironline.net>
Sent: Thursday, June 25, 2020 9:41 PM
To: Rotary motors in aircraft <flyrotary@lancaironline.net> Subject: [FlyRotary] Re: BSFC change on staging
 
=1B$B"!=1B(B This message was sent from a non-UWYO= address. Please exercise caution when clicking links or opening attachment= s from external sources.


Hi there Steve
Thanks for your work here.
How do you measure the BSFC?
So you have a version of the EC software where you can still change the Sta= ging point MAP.
The BSFC is ~0.5 better unstaged. Is this due to better fuel-air mixing or = is something else at play?

Am I right in thinking that at an economy cruise, a BSFC change of 0.5 migh= t yield an approx 0.9G/hr ($5/hr) of fuel saving.
That might then argue for a Staging Point at the earlier 15.5=1B$B!I=1B(B M= AP to enable unstaged cruise rather than the locked in 20=1B$B!I=1B(B MAP o= f the current software version.

What is your thoughts and conclusion if you have reached any?

Thanks again Steve

Steve Izett

> On 26 Jun 2020, at 8:47 am, Steven W. Boese SBoese@uwyo.edu <flyrot= ary@lancaironline.net> wrote:
>
> I ran a test on my engine stand with staged and unstaged fuel injector= s but with the same fuel flow and MAP.  The results are shown in the a= ttached image.  The engine is a 2010 2nd generation Renesis 6 port fro= m an automatic transmission car with the high RPM ports blocked off and stock fuel injectors.  The reduction drive = ratio is 3.18:1.  The prop is a 3 blade 72" Warp Drive and was op= erating just below stalled RPM.  A turbo is installed but no boost was= used in the test.  No attempt was made to operate at minimum BSFC.
>
> Steve Boese
> <BSFC.jpg>--
> Homepage:  http://www.flyro= tary.com/
> Archive and UnSub:   http://mail.lancaironline.net:81/lists/flyrotary/List.html


--
Homepage:  http://www.flyrotary.= com/
Archive and UnSub:   http://mail.lancaironline.net:81/lists/flyrotary/List.html
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